Gas turbine engine method for gas turbine engine testing (versions) method for production of gas turbine engine batch (versions) method for gas turbine engine operation

FIELD: engines and pumps.

SUBSTANCE: group of inventions presents the methods for gas turbine engine (GTE) testing. The test is done with measurement of engine operation parameters at different modes within programmed range of flight modes for certain engine series and bringing the obtained parameters to standard atmospheric conditions regarding the changing of working body properties and geometrical characteristics of air-gas channel at atmospheric conditions measuring. For this purpose there preliminary is created and corrected the engine mathematical model by the results of tests of sufficient engine number, which helps to define engine parameters at standard atmospheric conditions and different temperatures within accepted program. Parameters' actual values are referred to the standard ones, correction coefficients to measured parameters are calculated. The calculation of the latter is done by multiplying the measured values by the deviation of actual value from the norm regarding the correction coefficients. The developed test versions can be used at finishing, pilot and industrial, serial production and at the stage of aircraft engine operation, including after haul and providing more correct bringing of engine parameters obtained by experiment regarding the accepted engine control programs to parameters corresponding to the standard atmospheric conditions and increasing the representation of test results for complete range of flight cycles of engine operation.

EFFECT: increase of reliability results of defining the most important engine operation parameters in wide range of temperature climatic conditions at reduction of labour intensity and energy consumption and maintaining engine service life at testing.

10 cl

 

The group of inventions so linked as a single creative idea relates to the field of aircraft engine industry, namely to aircraft gas turbine engines of the type, methods of testing, pilot and industrial production and operation.

Known gas turbine engine made of double-circuit, includes a housing placed in it turbo-compressor unit comprising a compressor and turbine high and low pressure, at least one main combustion chamber, a jet nozzle system air supply and air cooling, hydraulic, fuel and lubrication systems, and monitoring systems and engine management (kliachkin A.L. Theory of air-jet engines. - M.: Mashinostroenie, 1969, str-396).

There is a method of testing gas turbine engine, taking into account seasonal factors testing, including prescribed in the technical specifications operating time maximum traction on a stationary mode and variable modes with access to the specified maximum thrust with the current during the test the temperature of atmospheric air. In the final stage of testing the engine output at maximum thrust, increase the temperature of the air entering the engine to a value greater than the outer temperature of 50-180C, and give additional time and enhance the performance communications outputs for maximum thrust (EN 2210066 C1, publ. 10.08.2003).

The known method development and testing of aircraft gas turbine engines, which consists in measuring the parameters on engine operating conditions and bringing them to standard atmospheric conditions, taking into account changes in the properties of the working fluid and geometric characteristics of the flow part of the engine when changing atmospheric conditions (Waitwindow, Vojnovic. Characteristics and performance properties of aircraft turbojet engines. M: mechanical engineering, 1979, 288 S., str-137).

There is a method of developing and testing aircraft engine type gas turbine, including the development of preset modes, the control parameters and the assessment of the resource and reliability of the engine. To reduce the time of testing, the final design of the engines 10-20% of the tests carried out with the gas temperature before the turbine exceeding the maximum operating temperature of 45-65C (SU 1151075 A1, publ. 10.08.2004). A known method for industrial production of aircraft gas turbine engines of the type including manufacturing and factory Assembly of power, control, command and Executive units, units and systems of the engine, including a compressor, turbine, combustion chamber, air, fuel and oil system and engine management system (Kartashov, VA, Cachan YA, Dolmatov A.I., Brain SCI, Korenevsky A Technology of production of aircraft engines. Zaporozhye: Motor Sich, 2009 [textbook.]; 4.4 Assembly of aircraft engines. Section 3, p.26-61.

The known method of operation of aircraft engines type CCD, which includes operations training, periodic inclusion, engine operation, periodic maintenance, repairs and renewals (Waitwindow, Vojnovic. Characteristics and performance properties of aircraft turbojet engines. M: mechanical engineering, 1979, s-137).

The General disadvantages of the known technical solutions are increased labor and energy consumption testing and insufficient reliability evaluation of engine thrust in a wide range of modes and regional temperature and climatic conditions due to non-maturity programs bring concrete results of tests carried out at different temperature and climatic conditions, the results related to the standard conditions of the atmosphere, by known methods, which do not take into account with sufficient correctness change settings and modes of operation depending on the adopted programs, adequate flight cycles, characteristic for the specific purpose of developing a mass-produced aircraft gas turbine engine, which makes it difficult given the Oia experimental test parameters to the parameters the relevant conditions in standard atmosphere at every stage of development, experimental, industrial, mass-production and operation of aircraft gas turbine engines.

The objective of the invention is to improve the reliability of the determination obtained by the test data on the statistical boundaries and possible changes in the magnitude of thrust of aircraft gas turbine engines at all stages, from debugging to mass industrial production and operation of various programs and various temperature and climatic conditions, as well as to provide opportunities for correctly aligning the obtained results to the standard conditions of the atmosphere and through them to any other real temperature and climatic conditions, taking into account the adopted software management engine and to increase the representativeness of the test results for the full range of the listed situations in relation to flight the engine cycles in training and combat conditions in different regions and seasonal the periods of operation.

The task in terms of method of testing gas turbine engine in the first embodiment is solved by the fact that according to the invention for the testing of gas turbine engine spend in different modes, parameters of which correspond to the parameters of the flight modes in the range supergra is certified for a particular series of engines measure and carry out the conversion of the received parameter values to standard atmospheric conditions, taking into account changes in the properties of the working fluid and geometric characteristics of the flowing part of the gas turbine engine when changing atmospheric conditions, with pre-create a mathematical model of the gas turbine engine, adjust it according to the results of bench tests of a representative number from three to five identical gas turbine engines, and then a mathematical model to determine the parameters of the gas turbine engine at standard atmospheric conditions and different temperatures of atmospheric air from the specified operating temperature range test bench based on the accepted programme regulation of the motor at maximum and forced modes, and the actual parameter values at specific temperatures atmospheric air each mode of testing refer to the parameter values at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature, and the conversion of measured parameters to standard atmospheric conditions is performed by multiplying the measured values by the coefficients, taking into account the deviation of atmospheric pressure from the standard and the correction factor, the dependence of the measured values from the atmospheric temperature registered at a particular testing gas turbine engines.

The task in terms of method of testing gas turbine engine according to the second variant is solved by the fact that according to the invention for the testing of gas turbine engine is carried out with the measurement of the parameters of its operation in different modes, parameters of which correspond to the largest and limiting values of the parameters of the flight modes in the range programmed for a specific series of engines, and carry out the conversion of the received parameters to standard atmospheric conditions, taking into account changes in the properties of the working fluid and geometric characteristics of the flow part of the engine when changing atmospheric conditions, with pre-create a mathematical model of the engine, adjust it according to the results of bench tests of a representative number from three to five engines, and then according to the mathematical model to determine the parameters of the engine at standard atmospheric conditions and different temperatures of atmospheric air from the specified operating temperature range test bench based on the accepted programme regulation of the motor at maximum and forced modes, and the actual value of the parameters at specific temperatures of atmospheric air in each mode of the test refer to the parameter values at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature, and the conversion of measured parameters to standard atmospheric conditions is performed by multiplying the measured values by the coefficients, taking into account the deviation of atmospheric pressure from the standard and the correction factor, reflecting the dependence on temperature of the atmospheric air, which is registered for specific tests, and taking into account the received data to perform a subsequent cycle test with a loaded engine, during which assess changes in parameters.

Thus, at least part of test cycles can be performed without heating the mode "low gas" after startup.

The task in terms of mode of production batch of gas turbine engines, which perform an experimental batch of the CCD, while mount chassis and powertrain engine including a compressor unit, turbine, jet nozzle, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, units and systems, and test assembled an experienced GTD, is solved by the fact that according to the invention tests produce any of the above testing methods for determining the actual characteristics of the resource and reliability of the engine, completed the drop test program will analyze the received results eliminate the deficiencies, if necessary, make changes in the design or in the individual nodes of the CCD and is considered a prototype is made and appropriate given program.

The task in part of the gas turbine engine decides that the engine according to the invention is made shaft, includes a housing placed in it by the compressor unit, at least the main combustion chamber, turbines, high and low pressure, jet nozzle, in addition, the engine includes an air system, as well as hydraulic - fuel and oil system, and the system current monitoring operation of all units of the engine, the control system comprising blocks collection, online processing of the current working information by issuing the commands, controls and subordinate Executive units and aggregates of these systems, with the engine tested any of the above described test method for determining the actual characteristics of the resource and reliability of the engine, at least one of the stages, namely stages of development, or as part of the party engines serial industrial production, and/or tested during operation after overhaul.

When this gas turbine engine can be made double-shaft and is equipped with an afterburner chamber SGAs the project.

Gas turbine engine can be performed three to contain the compressors and turbines of low, medium and high pressure jet nozzle with a variable thrust vector.

Hydraulic oil system of the engine can be equipped with two pump groups, spreading the oil pipework and nozzles, feed lubricating fluid to the friction elements of the nodes, including the possibility of providing an uninterrupted supply nodes lubricating fluid, including modes of inverted flight of the aircraft and the relevant provisions of the engine.

The task in terms of mode of production batch of gas turbine engines, in which at least a production factory Assembly of engines, each engine mount to the chassis and powertrain of the engine, including compressors, turbines, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, blocks and systems and make a bench test serial gas turbine engines from the party identically produced GTE, is solved by the fact that according to the invention the test subject, at least one engine of the industrial party GTE and produce test any of the above-described way is testing the basic operation settings serial industrially produced by the engine and verify compliance with specified values of the actual parameters of the engine with the subsequent transfer of results tests obtained in specific atmospheric and climatic conditions, to values corresponding to standard atmospheric conditions, with the possibility of subsequent conversion of the end results, if necessary, to any other desired atmospheric and climatic conditions, which is a particular serial engine or party simultaneously produced identical gas turbine engines with the ability to make the information in the technical documentation of the engine. The task in terms of method of operating a gas turbine engine, in which each time before you start perform a readiness check of the engine to work, run, warm-up and output of the engine to be specified in the bylaws operating modes, periodically make routine inspections, repairs, and at least one major repair, is solved by the fact that according to the invention after the overhaul, the engine is subjected to bench testing any of the above methods of testing for compliance with required parameters to bring the test results to the conditions of the standard atmosphere, if necessary, make the post-repair adjustments and/or re-testing, and conversion results to the specified temperature and the subsequent modes perfo the operation using the mathematical model of the gas turbine engine and methods of bringing any parameters described above.

The technical result provided developed by the totality of features and characteristics of a group of inventions is to provide enhanced reliability testing and computational determination of traction and other important operating characteristics of aircraft gas turbine engines due to less energy - and labour-receiving and more accurate casts experimentally obtained parameters of the engine to the parameters corresponding to the standard atmospheric conditions, and to increase the representativeness of the test results for the full range of flight cycles in climatic conditions of different regions taking into account seasonal variation of engine operation. This achieves the fact that prior to testing, create a mathematical model of the engine. Conduct testing of a representative number of usually three to five engines developed by the program and range of test conditions. Test results correct mathematical model, whereby on the basis of the following tests at specific temperatures determine the parameters of the engine at standard atmospheric conditions and different temperatures in the amount of the approved programs. The actual parameter values refer to the standard, calculate the correction factors to the measured parameters, when the eat the cast last performed by multiplying the measured values by the deviation of the fact from the norm, taking into account correction factors. This allows to simplify the subsequent tests to increase the accuracy and to extend the representativeness of the evaluation of the most important characteristics in the first place, and thrust at all the stages of creating, debugging, serial industrial production and flight operation of gas turbine engines with the correct distribution representative estimates on a wide range of regional and seasonal conditions subsequent flight the engine operation to be performed in accordance with the invention.

Testing of gas turbine engine spend in different modes with parameters corresponding to the parameters of the flight modes on the program for a particular series of engines. During the tests measure and carry out the conversion of the received parameter values to standard atmospheric conditions. Bringing produce to reflect changes in the properties of the working fluid and geometric characteristics of the flowing part of the gas turbine engine when changing atmospheric conditions. For this purpose, we first create a mathematical model of the gas turbine engine of the type, for example, see Waitwindow, Vojnovic. Characteristics and performance properties of aircraft turbojet engines. M: mechanical engineering, 1979, p.90-91, 106-107. Adjust it according to the results of bench tests of a representative number from three gopati identical gas turbine engines. Then a mathematical model to determine the parameters of the gas turbine engine at standard atmospheric conditions and different temperatures of atmospheric air within the programme for testing of the engine at maximum and forced modes. The actual parameter values at specific temperatures of atmospheric air in each mode of the test refer to the parameter values at standard atmospheric conditions. Calculate correction factors to the measured parameters depending on the atmospheric temperature. The conversion of measured parameters to standard atmospheric conditions is performed by multiplying the measured values by the coefficients, taking into account the deviation of atmospheric pressure from the standard, and a correction factor reflecting the dependence of the measured values from the atmospheric temperature registered at a particular testing gas turbine engines.

In another embodiment, the test gas turbine engine is carried out with a sequential set of actions the previous version. Then taking into account the received data additionally perform subsequent cycle test with the highest loading of the engine, including quick access to the maximum or full-power mode, a quick reset on reimage gas with engine shutdown. Quick access to the maximum or forced modes, at least part of the overall test cycle is carried out in the pace of pick-up and discharge in relation to flight cycles for combat and training applications gas turbine engine.

If necessary, increase volumetric accuracy range of test modes, at least up to 20% of cycles testing of gas turbine engine can be performed without heating in the idling mode after startup.

In the production method of the party of gas turbine engines have experienced party GTE. Produce, at least, the Assembly of each of the experimental engine. Mount the chassis and powertrain of the engine, including a compressor unit, turbine, jet nozzle, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, units and systems. Test mounted the experienced CCD. Trials produce any of the above described test method for determining the actual characteristics of the resource and reliability of the engine. Upon completion of the test program to analyze the results. Eliminate the identified deficiencies. If necessary, make changes in the design or in the individual nodes of the CCD and is considered a prototype is made and comply with them given program.

Gas turbine engine made shaft, includes a housing placed in it by the compressor unit, at least the main combustion chamber, turbines high and low pressure jet nozzle. The engine includes an air system, as well as hydraulic - fuel and oil system, and the system current monitoring operation of all units of the engine, the control system comprising blocks collection, online processing of the current working information by issuing the commands, controls and subordinate Executive units and units of the listed systems. The engine tested any of the above described test method of the CCD on the actual characteristics of the resource and reliability of the engine, at least one of the stages, namely stages of development, or as part of the party engines serial industrial production, and/or tested during operation after overhaul.

However, at least two-shaft gas turbine engine variant is equipped with afterburner combustion chamber and a jet nozzle with a variable critical section and the thrust vector.

Gas turbine engine made three contains the compressors and turbines of low, medium and high pressure and at least one jet nozzle with a variable thrust vector.

For whom the devices stable operation in an inverted position, typical long-haul flight of the aircraft (LA) when performing aerobatics or in battle conditions, the gas turbine engine may be equipped with a modified hydraulic oil system. This system is equipped with two pump groups, spreading the oil lines and systems, injector, feed lubricating fluid to the friction elements of the nodes. These provide the opportunity for an uninterrupted supply nodes lubricating fluid in these extreme modes of engine operation.

In the production method of the party of gas turbine engines operate at least a production factory Assembly engines. Each engine is mounted to the chassis and powertrain of the engine, including compressors, turbines, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, units and systems. Produce bench test serial gas turbine engines from the party identically manufactured by GTE. Test expose the group to engines of the industrial party GTE and produce test any of the above described method of test for determination of main parameters serially produced industrial engine and verify compliance with specified values, the actual the ski operation parameters of the engine. Then translate the test results obtained in specific atmospheric and climatic conditions, to values corresponding to standard atmospheric conditions, with the possibility of subsequent conversion of the end results, if necessary, to any other desired atmospheric and climatic conditions, which is a particular serial engine or party simultaneously produced identical gas turbine engines. Make information in the technical documentation of the engine.

In the method of operating a gas turbine engine before each run perform a readiness check of the engine to work. Run, warm-up and output of the engine to be specified in the bylaws operating modes. Periodically make routine inspections, repairs, and at least one major overhaul. After the overhaul, the engine is subjected to bench testing any of the above described method of testing for compliance with required parameters to bring the test results to the conditions of the standard atmosphere. If necessary, make the post-repair adjustments and/or re-testing. Recount results to the specified temperature and the subsequent modes of operation with the use of a mathematical model of the gas turbine is of vegetale and techniques to bring any parameters described above.

Testing of aircraft gas turbine engines produce on the stages of development, experimental and industrial production and operation as follows.

An example of the method for testing gas turbine engine (GTE).

The test is subjected to a representative group of three to five GTE. Using previously developed mathematical model of the engine. Tests the specified group GTE carried out at a temperature tI=0C,

VA=745 mm Hg

The results of measurements and their statistical generalization get the values of the parameters: thrust engine R=985 kgf and the rotational speed n=98,8%.

For the further evaluation of test results using the mathematical model of the engine, which they calculate parameters for different modes of operation in the temperature range inlet air to the engine, including at tI=+15C. the results of the calculation are shown in table 1.

Table 1
tI, C
The temperature at engine inlet-150 +15+30
R, kgf1000980970950
The thrust force
n %
speed9899100100

Compare the received data and calculates correction coefficients by the ratio of the parameter value at tI=+15C to parameter values in a given range of temperature at engine inlet (Table 2).

Table 2
tI, C-150+15+30
KR0,970,9911,021
Kn1,021,0111

Then determine the parameters under standard atmospheric conditions (ISA)

,

nMCA=nKn=98,81,01=99,79%

and make the resulting data to supporting documentation of an appropriate group of GTE.

Use the above parameters of the CCD to calculate corresponding parameters according to temperature and climatic conditions specific areas of operation of the engines in the range of working temperatures tI=50C. Extreme for the specified temperature range parameter values GTE, based on test results using mathematical models and data at standard atmospheric conditions (ISA), are presented in Table 3 and Table 4.

Table 3
tI, C
The temperature at engine inlet-50-15 0+15+20+50
R, kgf12001000980970950900
The force from thrust
n %969899100100100
speed

0,81
Table 4
tI, C-50-150+15+20+50
KR0,970,9911,0211,078
Kn1,0421,021,01111

From Table 3 and table 4 shows that pull in extreme temperature range (-50)C to (+50)C is changed to one third when changing speed by 4%.

Thus, the invention improves the reliability of the results of the testing of gas turbine engines with regard to the adopted management programs.

The above sequence of tests of the CCD is used at all stages from finishing to industrial production, operation, and overhaul aircraft gas turbine engines.

1. The method of testing gas turbine engine (GTE), characterized in that the test gas turbine engine spend in different modes, parameters of which correspond to the parameters of the flight modes in the range programmed for a specific series of engines, measure and implement the conversion of the received parameter values to standard atmospheric conditions, taking into account changes in the properties of the working fluid and g is americasa characteristics of a flowing part of the gas turbine engine when changing atmospheric conditions, when this pre-create a mathematical model of the gas turbine engine, adjust it according to the results of bench tests of a representative number from three to five identical gas turbine engines, and then a mathematical model to determine the parameters of the gas turbine engine at standard atmospheric conditions and different temperatures of atmospheric air from the specified operating temperature range test bench based on the accepted programme regulation of the motor at maximum and forced modes, and the actual parameter values at specific temperatures of atmospheric air in each mode of the test refer to the parameter values at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature, and the conversion of measured parameters to standard atmospheric conditions is performed by multiplying the measured values by the coefficients, taking into account the deviation of atmospheric pressure from the standard and the correction factor, reflecting the dependence of the measured values from the atmospheric temperature registered at a particular testing gas turbine engines.

2. The method of testing gas turbine engine, characterizing the I, what testing gas turbine engine is carried out with the measurement of the parameters of its operation in different modes, parameters of which correspond to the largest and limiting values of the parameters of the flight modes in the range programmed for a specific series of engines, and carry out the conversion of the received parameters to standard atmospheric conditions, taking into account changes in the properties of the working fluid and geometric characteristics of the flow part of the engine when changing atmospheric conditions, with pre-create a mathematical model of the engine, adjust it according to the results of bench tests of a representative number from three to five engines, and then a mathematical model to determine the parameters of the engine at standard atmospheric conditions and different temperatures of atmospheric air from the specified operating temperature range test bench based on the accepted programme regulation of the motor at maximum and forced modes, and the actual parameter values at specific temperatures of atmospheric air in each mode of the test refer to the parameter values at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature, and the conversion of the measured PA is amerov to standard atmospheric conditions is performed by multiplying the measured values by coefficients taking into account the deviation of atmospheric pressure from the standard and the correction factor, reflecting the dependence on temperature of the atmospheric air, which is registered for specific tests, and taking into account the received data to perform a subsequent cycle test with a loaded engine, during which assess changes in parameters.

3. The method of testing gas turbine engine according to claim 2, characterized in that at least part of test cycles exercise without warming up at the idling after startup.

4. The production method of the party of gas turbine engines, which perform an experimental batch of the CCD, while mount chassis and powertrain engine including a compressor unit, turbine, jet nozzle, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, units and systems, and test assembled an experienced GTD, characterized in that the tests produced by the method according to any one of claims 1 to 3 to determine the actual characteristics of the resource and reliability of the engine, analyze the results, eliminate the identified deficiencies.

5. Gas turbine engine, characterized in that the shaft, includes a housing placed in it compress rim unit, at least, the main combustion chamber, turbines, high and low pressure, jet nozzle, in addition, the engine includes an air system, hydraulic fuel and malinow system and the current system of monitoring the operation of all units of the engine, the control system comprising blocks collection, online processing of the current working information by issuing the commands, controls and subordinate Executive units and units mentioned above, when the engine is tested by the method according to any one of claims 1 to 3 to determine the actual characteristics of the resource and reliability of the engine, at least one of the stages and it is in the stages of development, or as part of the party engines serial industrial production, and/or tested during operation after overhaul.

6. Gas turbine engine according to claim 5, characterized in that the shaft and is equipped with an afterburner combustion chamber.

7. Gas turbine engine according to claim 5, characterized in that the three, contains the compressors and turbines of low, medium and high pressure jet nozzle with a variable thrust vector.

8. Gas turbine engine according to claim 5, characterized in that the hydraulic oil system the engine is equipped with two pump groups, spreading the oil pipework and nozzles, under the sponding lubricating fluid to the friction elements of the nodes, including the possibility of providing an uninterrupted supply nodes lubricating fluid, including modes of inverted flight of the aircraft and the relevant provisions of the engine.

9. The production method of the party of gas turbine engines, in which at least a production factory Assembly of engines, with mount chassis and powertrain engine, including compressors, turbines, at least one combustion chamber, air and fuel and hydraulic oil systems, monitoring, command and control elements, blocks and systems and make a bench test serial gas turbine engine from the party identically produced GTE, characterized in that the test subject, at least one engine of the industrial party GTE and produce the test method according to any one of claims 1 to 3 determination of the basic parameters serially produced industrial engine and verify compliance with specified values of the actual parameters of the engine with the subsequent transfer of the test results obtained in specific atmospheric and climatic conditions, to values corresponding to standard atmospheric conditions, with the possibility of subsequent conversion of the end results, if necessary, to any others who shM required atmospheric and climatic conditions, for which is a particular serial engine or party simultaneously produced identical gas turbine engines with the ability to make the information in the technical documentation of the engine.

10. A method of operating a gas turbine engine, in which each time before you start perform a readiness check of the engine to work, run, warm-up and output of the engine to be specified in the bylaws operating modes, periodically make routine inspections, repairs, and at least one major overhaul, characterized in that after the overhaul, the engine is subjected to bench testing the method according to any one of claims 1 to 3 for compliance with required parameters to bring the test results to the conditions of the standard atmosphere, if necessary, make the post-repair adjustments and/or re-testing, and conversion results to the specified temperature and modes post-repair operation using the mathematical model of the gas turbine engine and methods of casting parameters by the method according to any one of claims 1 to 3.



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: before firing test in gang with solid-propellant rocket engine, nozzle or elastic support hinge defining axial strain of nozzle moving part, are subjected to pressure varying in the range of pressure variation in engine combustion chamber at bench fire test to measure moving part axial yield. Said axial yield is used to define nozzle turn angle caused by said yield. Then, at zero pressure ahead of the nozzle, it is driven from zero angle to maximum angle to measure travel of drive rod, force in drive kinematics and nozzle angle. Measured values are used to define additional change in nozzle turn angle caused by play as drive travel at zero force and actual yield of structural elements as relationship between the difference between design angle for absolutely stiff kinematics and measured angle and measured force. Now, at fire test, obtained results of measurements are used to define nozzle turn angle with due allowance for yield, play and structure compliance.

EFFECT: higher accuracy.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: group of inventions describes test method of GTE for gas dynamic stability by means of the developed inlet aerodynamic device provided with a retractable intercepter and a graduated scale with fixation of boundary and intermediate positions in the air flow with various degree of aerodynamic shading and disturbance of the flow in full range of 0 to 100%. The developed versions of experimental evaluation of gas dynamic stability have been used during pilot, pilot-industrial and batch production and at the stage of operation of aircraft engines and improve evaluation reliability of gas dynamic stability, determination of the boundaries of the engine transition to surging, and safety margin of 2-5% of the critical value is set.

EFFECT: use of the group of inventions opens new possibilities of conducting tests for gas dynamic stability both at the stage of production and adjustment of a test specimen of the engine, and at the stage of performance of proof test immediately at industrial production and operation of engines, including after the overhaul with the test effectiveness providing the best quality of the engine at all stages.

15 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: test methods of jet-turbine engines (JTE) are described in the group of inventions. When performing the test steps, alteration of the modes, which exceed as to duration the programmed flight time, is performed. Typical flight cycles are formed, based on which damageability of the most loaded parts is determined as per the programme. The required number of loading cycles during the test is determined. Full scope of tests is formed, including a quick change of cycles in the complete register from quick selection of maximum or full augmented power mode of the engine, and then, representative cycle of continuous operation with multiple alteration of modes in the whole working spectrum with various span of range of the mode change, which exceeds the flight time at least by 5-6 times. Quick selection of maximum or augmented power mode in some part of the test cycle is performed at the rate of acceleration and discharge.

EFFECT: development of test methods of aircraft jet-turbine engines with improved reliability of test results at any of the steps from an experimental-industrial specimen to industrial production and flight operation of aircraft engines.

8 cl

FIELD: heating.

SUBSTANCE: method for determining the technical state of domestic refrigerating equipment is described, which involves measurement of temperatures in its compartments, measurement of time of the compressor operation, in which the technical state of domestic refrigerating equipment is evaluated as per the speed of temperature decrease in its compartments at the specified time interval of the compressor operation or as per the time interval from actuation till the specified temperature value is achieved in compartments.

EFFECT: providing independent process for determination of the technical state of domestic refrigerating equipment; improving evaluation reliability.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to ICE servicing, particularly, to diagnostics of ICEs. Proposed method consists in measuring full vacuum pressure Pfv and engine compression Pc for, at least, one cylinder of tested ICE before and after decoking. Obtained values are compared. If said values differ not more than by 10% residual life is defined. For this, basic graphical dependence of variation of Pfv upon Pc is plotted and dependence of sleeve assembly consumed life associated therewith. Pfv and Pc values measured in the last dry starting are plotted on said curve. Position of said plotted points relative to basic graphical plot is used to define residual life of sleeve assembly for at least one cylinder.

EFFECT: fast determination.

4 cl, 1 dwg, 1 tbl

FIELD: engines and pumps.

SUBSTANCE: invention relates to ICE servicing, particularly, to diagnostics of ICEs. Proposed method consists in measuring residual vacuum pressure Prv and engine compression Pc for, at least, one cylinder of tested ICE before and after decoking. Obtained values are compared. If said values differ not more than by 10% residual life is defined. For this, basic graphical dependence of variation of Prv upon Pc is plotted and as well as sleeve assembly consumed life curve associated therewith. Prv and Pc values measured in the last dry starting are plotted on said curve. Position of said plotted points relative to basic graphical plot is used to define residual life of sleeve assembly for at least one cylinder.

EFFECT: fast determination.

1 dwg, 1 tbl, 4 cl

FIELD: electricity.

SUBSTANCE: method is carried out by measurement of current values in two points of its shorting ring spaced relative to each other by the value of a pole division of the induction motor or multiple to it, for this purpose on the shorted ring of the rotor in the specified points there are two current sensors installed. Values of currents flowing in the shorting ring of the rotor certify availability or absence of motor damages.

EFFECT: provision of the possibility for continuous simultaneous diagnostics of electric and mechanical damages of an induction motor with a short-circuit rotor during motor operation.

FIELD: measurement equipment.

SUBSTANCE: measuring device of impulse reactive thrust of low thrust liquid propellant engines (LT LPE) contains a heavy rig installed by means of shock absorbers on a power support of the test bench, a loading frame, to which a force transmitting frame for attachment of LT LPE is connected, which are installed coaxially and have the possibility of being moved relative to the rig along the main measurement axis of the device, two belts that are adjustable as to length and flexible as to the main measurement axis and transverse suspensions arranged perpendicular to it and connected with some of their ends to the rig, as well as setting device of calibration force of reference of static force and an operating dynamometer, which are installed coaxially to the main measurement axis of the device and axis of LT LPE. The loading frame has a closed and a stiff shape in the form of front and rear traverses connected by means of tie rods, located on opposite sides of the rig, to which the other ends of flexible transverse suspensions are connected; at that, the force transmitting frame is fixed on the outer side of front traverse of the loading frame, and the calibration force setting device is installed on its inner side. Spherical hinge of its power output stock interacts with the rig, on the opposite side of which the operating dynamometer is installed, with which the spherical hinge of force receiving stock fixed on rear traverse of the loading frame interacts.

EFFECT: improving the device accuracy and operability.

3 cl, 4 dwg

FIELD: measurement equipment.

SUBSTANCE: diagnostics method of the technical state of inter-rotor bearing of two-shaft gas turbine engine (GTE) involves measurement of vibration signals in steady-state rotation mode of high pressure rotor (HPR) of not less than 90% of its maximum rotation speed, recording of vibration signals from GTE housing structures with their further conversion to amplitude-frequency spectrum, allocation in that spectrum of separating frequency of inter-rotor bearing and rotation speeds of low pressure rotor (LPR) and HPR with further determination of available defect of inter-rotor bearing. In order to improve diagnostics reliability of the state of inter-rotor bearing of two-shaft gas turbine engine, precipitation and propagation of a defect is determined upon achievement of value of amplitude level of separating frequency of not less than 2 mm/s and not more than half of the amplitude level of LPR and HPR rotation speed that is maximum as to amplitude, and availability of propagated defect is determined upon achievement of the value of amplitude level of the separating frequency of not less than 2 mm/s and more than half of the amplitude level of LPR and HPR rotation speed that is maximum as to amplitude, at simultaneous occurrence of difference frequencies (n2-fc) and/or (fc-n1), and/or (2*fc-n1), and/or (2*fc-n2), and/or (2*n1-fc), which stand out clearly out of the noise level, where n1 - LPR rotation speed (Hz), n2 - HPR rotation speed (Hz), fc - separator rotation speed (Hz).

EFFECT: early detection of defects during GTE manufacture, operation, maintenance or repair.

3 cl, 5 dwg

FIELD: oil and gas industry.

SUBSTANCE: diagnostics method of pump units of main oil line involves investigation of a frequency spectrum of the received signal and its interpretation. The required signal is received immediately from the oil line that serves as a signal transmission channel; then, time history of spectrum of the received signal is analysed and compared to frequency of reference signal, thus determining failures of pump units.

EFFECT: improving accuracy and reliability during diagnostics of the state of pump units of main oil line.

1 dwg

FIELD: electric engineering.

SUBSTANCE: device has electric generator connected cinematically with internal combustion engine, single-armature converter, controlled constant-voltage source, and controlled constant-voltage converter. Input of controlled constant-voltage converter is connected with output of constant voltage electric generator and output of the converter is connected with single-armature converter through diode. Voltage of controlled constant-voltage converter together with voltage dc electric generator exceeds voltage of single-armature converter. Control of load of tested Diesel-generator is provided by changing voltage of controlled constant-voltage converter. Constant voltage controlled converter allows to compensate influence of change in speed of tested Diesel-generator to preset under-load operation.

EFFECT: ability to control speed of Diesel-generator in wide range.

1dwg

FIELD: testing of engines.

SUBSTANCE: device comprises capacitive electronic marker of cylinder number and pulse multiplying device, which multiplies signals proportional to the current consumed by the starter and voltage drop at the terminals of the storage battery when the engine is actuated with the starter. The curve obtained at the output of the device is directly proportional to the curve of variation of compression throughout the cylinders of the engine. The first input of the pulse multiplying device is connected with the output of shunting resistance (current sensor) through a differential amplifier and voltage divider. The second input is connected with the voltage divider. The shunting resistance is connected with the wire which connects the positive terminal of the storage battery with the starter. The output of the pulse multiplying device is connected with the first input of the adder through the RC-circuit and voltage follower . The second input is connected with the output of the electronic marker of cylinder number.

EFFECT: enhanced accuracy of measuring compression.

FIELD: testing of engines.

SUBSTANCE: device comprises systems for parametric, vibration, visual-optical, operating life, and expertise diagnosing of the gas-pumping assembly connected with the unit for generating list of limiting parameters of gas-pumping assembly operation. The device is additionally provided with units and subsystems for generating time schedules of the necessity of repairing the gas-pumping assembly, defect lists, orders on the replacement parts, volumes and types of the repairing materials, and calculation of cost and time of repairing..

EFFECT: enhanced accuracy of diagnosing.

1 dwg

FIELD: engine construction; measurement technology.

SUBSTANCE: internal combustion engine is subject to inspection by means of continuous finding of indicator diagram of cylinder depending on angle of rotation of shaft or from time due to stresses induced in studs or bolts that fix head of assembly of cylinders. Diagram and its digital characteristics are compared with reference ones. Indicator diagram of cylinder is achieved by means of preliminary built calibration dependence, which was built simultaneously from current values of stresses and pressures in cylinder at no less than three values of angles of rotation of shaft. Indicator diagram is used to calculate digital characteristics and to compare them with reference ones to determine technical condition of engine.

EFFECT: improved precision of diagnostics of technical condition of engines.

4 cl, 3 dwg

FIELD: aviation technology.

SUBSTANCE: analog data coming from nozzles for measuring pulsation of total and static pressures which nozzles are mounted at input and output of compressor to speed pulsation measuring unit. Simultaneously pressure pulsation is measured above blades of working wheel. Data on pulsation enters sync input and registration unit. Analog signals are introduced by means of sync input and registration unit for subsequent processing of fast-changing pressures to build isobars visualizing structure of flow in rotating working wheel during time periods corresponding to time needed for passing each interblade channel and each blade. Sizes of edge gaps are measured, angles of blades mounting are calculated, speed of flow in absolute motion at output and input of compressor is determined after measurements are completed synchronously.

EFFECT: improved precision of measurement.

2 cl, 5 dwg

FIELD: running ground repair of bypass gas-turbine engines; replacement of front case of fan module.

SUBSTANCE: proposed method includes dismantling of engine and replacement of defective front case of fan. Technological ring is mounted and technological plunger is placed along axis of engine; said plunger is provided with bracket and dial indicator. By rotating the plunger, end play of surface of technological ring relative to axis of rotation of plunger is measured by means of dial indicator. Then, partial dismantling of engine is performed, viz.: separation of afterburner with adjustable nozzle, mixer housing with rear case of second loop, body of turbine supports together with cone, low-pressure turbine rotor and fan fairing with inductor. Technological ring is mounted on rear flange of low-pressure turbine nozzle assembly. Technological plunger is mounted in front and rear trunnions of fan rotor and bracket with dial indicator is secured on technological plunger near technological ring. Besides that, radial run-out of inner circular surface of technological ring relative to axis of rotation of plunger is measured. Defective front case of fan is replaced with standard one and again end play and radial run-out of technological ring surfaces are measured. If measurements are within tolerable limits, front case may be engaged with engine.

EFFECT: facilitated procedure of replacement of front case of fan.

2 cl, 3 dwg

FIELD: experimental hydrodynamics.

SUBSTANCE: submergible hydraulic drive has braking disks mounted on hubs instead of axially aligned screw propellers. Two face washers are coaxially mounted at the outer faces of disks with a spaced relation to each other. The washers are interconnected over periphery through ties for permitting axial space to be adjusted. The periphery interface zone of the washers receives rim washers which are mounted to provide an axial space between them and to form a casing with the rim which is penetrable for fluid in the radial direction. The axial space between the faces of the rim washers is equal or less than the thickness of the boundary layer on the face of the braking disk.

EFFECT: enhanced reliability.

1 cl, 2 dwg

FIELD: compressors; surge protection devices of turbocompressors.

SUBSTANCE: invention makes it possible to improve quality of diagnosing of surging, thus increasing sphere of practical application of equipment. Proposed method of diagnosing of surging is based on usage of covariation of signals from pickups whose measured parameters present surges with correlation. Used as criteria of revealing of surge is result of comparison pf parameter of surge equal to covariation of signals of measured parameter with threshold value. System to reveal surging contains compression parameters pickups 2 and 3 installed on compressor plant 1, low-pass filters 4, 5, and 9, summers 6 and 7, multiplier 8, comparator 10 and switch off delay element 11.

EFFECT: enlarged sphere of application.

9 cl, 2 dwg

FIELD: proposed method is used for testing forced injection internal combustion engines provided with electric control of fuel delivery without external loading of engine.

SUBSTANCE: proposed method includes measurement of number of free racing cycles during definite period of time. Engine operating at minimum idling revolutions is shifted to free racing mode by abrupt motion of fuel delivery control member to maximum position; fuel delivery is discontinued periodically when high limit crankshaft rotational speed is attained. As soon as rotational speed of engine crankshaft reduces to low limit, fuel delivery is cut-in. The magnitudes thus obtained are compared with standard ones for estimation of state of engine.

EFFECT: enhanced accuracy of testing.

1 dwg

FIELD: equipment for production, storage and transportation of oil and gas.

SUBSTANCE: method of usage includes incoming control of technical condition of production equipment before usage. Datum reference points are selected from parameters including points having limit values to create initial database for monitoring degradation processes in production equipment during total period of usage. The operation servicing, technical monitoring and diagnostics are conducted to reveal character of changes in reference points of equipment depending on mode and duration of usage. Technical monitoring is conducted in specific time period without shutting technological process down. Estimation of regressive processes is made taking meanings of reference points into account as well as analysis of usage conditions. Real values of parameters of reference points are compared with meanings of reference points of initially determined incoming control. In case the controlled parameters correspond to conditions of usage, the longer usage is declared. If the parameters do not correspond to the conditions then the urgent diagnostics should be conducted. During diagnosis real technical condition of production equipment is evaluated and conditions of prolongation of usage are defined, as well as risk of longer usage. Diagnosis determines necessity of repair works or unsuitability of equipment is declared. If production equipment is declared suitable for longer usage, then the declaration of production safe is developed.

EFFECT: improved truth of data; improved reliability of diagnosis.

Up!