Method of operational development of experimental jet turbine engine

FIELD: engines and pumps.

SUBSTANCE: invention relates to air-engine building, namely to air turbojets. The experimental double-circuit, two-shaft GTE is subjected to operational development. Operational development of TJE is performed step by step. At each phase from one to five TJEs are tested for compliance with the pre-set parameters. The program of tests with the subsequent finishing reworking includes tests of the engine for identification of influence of climatic effects on the change of operational performance of experimental JTE. Tests are performed with measurements of engine parameters at various operating conditions within programmed range of flight modes for particular engine range to reference measured parameters to standard atmospheric conditions with due allowance for variation of working body properties and geometric characteristics of engine air-gas channel.

EFFECT: improvement of turbojet performance, namely traction, experimentally tested resource and reliability of the engine by operation in the full range of flight cycles in various climatic conditions, and also in simplification of technology and reduction of labour costs and power consumption of turbojet test process at the phase of operational development of experimental TJE.

4 cl, 2 dwg

 

The invention relates to the field of aircraft engines, namely, to aircraft turbojet engines.

Known dual-circuit, two-shaft turbojet engine (turbojet), including turbo-complexes, one of which contains mounted on the same shaft as the compressor and the turbine low pressure and the other contains a similar joint on the other shaft, coaxial with the first compressor and high pressure turbine, an intermediate separator housing between said compressors, the outer and inner contours, main and afterburner combustion chamber, the mixing chamber of air flows of the working fluid and adjustable nozzle (N. N. Sirotin, etc. design principles of production and operation of aircraft gas turbine engines and power plants in the system of CALS technologies. Book 1. Moscow, ed. "Science." 2011, pp. 41-46, Fig.1.24).

Known turbofan engine, which is made of double-circuit, comprises a housing supported on the compressor and turbine, cooled combustion chamber, the fuel-pump group, jet nozzle and control system command and Executive bodies (Shulgin V. A., Haisyn S. Y. turbojet engines low-noise aircraft. M., ed. Engineering, 1984, pp. 17-120).

The known method of testing the final design AVI�operating turbojet engines, namely, in the measurement of the operating conditions of the engine and the reduction to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the engine when changing atmospheric conditions (Yu. a. Litvinov, V. O. Borovik. Characteristics and performance of aircraft turbojet engines. Moscow: mechanical engineering, 1979, 288 PP., pp. 136-137).

The known method of testing aircraft engine type turbojet, including the testing of a given mode, the control parameters and the assessment of resource and reliability of the engine. To reduce the test time while fine-tuning engines for 10-20% of the tests carried out with the gas temperature before the turbine exceeding the maximum operating temperature 45-65°C (SU 1151075 A1, publ. 10.08.2004).

Common disadvantages of these known technical solutions are increased labor and energy consumption testing and insufficient reliability of the estimation of thrust of the engine in a wide range of modes and regional temperature and climatic conditions due to nitrobutane programs bring specific results of tests performed at different temperature and climatic conditions to results classified under standard atmosphere conditions known methods, cat�who do not consider with sufficient correctness the change of parameters and modes of operation of the engine depending on the adopted programs, adequate flight cycles, which is characteristic for the specific purpose of developing a turbojet engine, which complicates the possibility of bringing experimental test parameters to the parameters corresponding to the standard atmosphere conditions.

Object of the invention is to provide a method of refining experimental turbojet engine, a set of technical solutions which provides improved traction and increased reliability operational characteristics for different temperature and climatic conditions of different regions and operating conditions of the engine, as well as to simplify the technology and reduce the labor costs and the intensity of the test process on the TRD debugging stage experienced TRD with increasing the representativeness of the test results for the full range of these situations in relation to flight cycles engine in training and combat conditions in different regions and seasonal operating periods.

The problem is solved in that in the method of refining experimental turbojet engine of the type according to the invention, subjected to fine-tuning by experienced engine, designed turbofan, twin-shaft, while the fine-tuning of the engine is produced in stages, which develop software and algorithms development testing, experienced TRD; at each stage is exposed to a�up testing for compliance with specified parameters statistically representative number, mainly, from one to five copies and carry out condition survey of each tested from the number of instances experienced engine; for the analysis and assessment of the state if necessary, make a takedown, followed by the possible revision and/or replacements of any of the modules and/or nodes of the CFR engine, inspect and if necessary replace modified any of the damaged or inappropriate tests required parameters module, including the compressor low pressure (CLP) with inlet guide vanes (IGV), which contains a power of the radial strut, consisting of fixed and controlled rolling elements and equally spaced in the plane of the inlet section with an angular frequency of placement of racks in range (3,0÷4,0) u/rad, and a rotor shaft, comprising, preferably, not more than four working wheels with a system of blades; a gas generator including assemblies, an intermediate housing, a high pressure compressor, a main combustion chamber and high pressure turbine; sequentially arranged behind the generator, coaxially mounted low pressure turbine; a mixer; the front device, the afterburner combustion chamber and connected to the afterburner combustion chamber of a variable jet nozzle; and mounted over the main� the combustion chamber in the external circuit module air-to-air exchanger if necessary, examining any no less than sixty tubular block-modules of the latter, in addition, examine and make the necessary fine-tuning gear boxes of motor units and combining these modules electrical, pneumatic, hydraulic fuel and oil systems, including, if necessary, replacement of sensors, command blocks, actuators and cables systems diagnostics and automatic control of the engine; wherein the test program with the subsequent development of the revision include a test engine to determine the influence of climatic conditions (UWC) on change in performance experienced TRD; for this test, not less than one, for representativeness, preferably, three to five experienced engine; the testing of the prototype engine is carried out in various modes whose parameters correspond to the parameters of the flight modes in the range programmed for a particular series of engines, make measurements and perform the conversion of the received parameter values to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the turbojet engine when changing atmospheric conditions, first create a mathematical model of t�breaching engine adjust it according to the results of bench testing of a representative number of three to five identical turbojet engines, and then according to the mathematical model to determine the parameters of the turbojet engine at standard atmospheric conditions and different temperatures of atmospheric air from a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes, and the actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of, and the conversion of the measured parameters to standard atmospheric conditions is carried out by multiplying the measured values by the factors, taking into account the deviation of the atmospheric pressure from the standard, and the correction coefficient reflecting the dependence of the measured values from the temperature of the atmospheric air, registered in the particular test turbojet engines.

Test TRD can carry out the measurement of the performance parameters for different modes, the parameters of which correspond to the largest and pre�individual parameter values of the flight modes in the range programmed for a particular series of engines, and carry out the conversion of the obtained parameters to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the engine when changing atmospheric conditions, first create a mathematical model of the engine, adjust it according to the results of bench testing 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 a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes, moreover, the actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of, as a conversion of the measured parameters to standard atmospheric conditions is carried out by multiplying the measured values by the factors, taking into account the deviation of the atmospheric pressure from the standard, and the correction coefficient reflecting the dependence�value from the temperature of the atmospheric air, registered with specific tests, and taking into account the obtained data, perform the following test cycle with the loading of the engine, which measure the change in the parameters.

Fine-tuning may be experienced engine, VNA KND which contains, preferably, twenty-three radial strut connecting the inner and outer rings VNA capable of transmitting loads from the outside of the motor housing on the front support, wherein at least a portion of racks aligned with the channels of the oil system, placed in a stationary element of the racks, with the possibility of supplying and discharging the oil, and venting of oil and premerlani cavities front bearing of the rotor KND.

Fine-tuning may be experienced TRD, the area of the frontal projection of the input aperture of FBX. Ave, BHA KND which geometrically defines the cross section of the inlet mouth of the intake canal, bounded on the larger radius of the inner contour of the outer ring VNA, and the smaller radius of the inner contour of the inner ring VNA, is made greater than the total area of the aerodynamic shadow FStcreated a front projection Coca and radial struts (2,54÷2,72) times and is (0,67÷0,77) on the full area of the circle FPLN.that is limited to a radius of the inner contour of the outer black�CA VNA in the plane of the input aperture.

The technical result provided by the given set of features is to provide a method of finishing turbojet engine with improved performance, namely thrust and increased reliability of these characteristics TRD due to a more reliable and accurate casts experimentally obtained parameters of the motor to the parameters corresponding to the standard atmosphere, as well as to enhance the representativeness of the results of tests conducted at the debugging stage experienced TRD for a full range of flight cycles in different climatic conditions. It is reach by the fact that in accordance with the invention prior to testing, create a mathematical model of the engine. Test a representative number of engines from the party experienced produced by TRD developed program for array of test modes. According to test results correct mathematical model, through which on the basis of subsequent tests at specific temperatures determine the parameters of the engine at standard atmospheric conditions and different temperatures. The conversion of measured values of parameters specific to standard tests carried out by the correction factors.

The technical result achieved and�the acquisition, to simplify further tests to improve the robustness and to extend the representativeness of the evaluation of the most important characteristics, primarily thrust with the correct distribution of representative estimates on a wide range of regional and seasonal conditions subsequent in-flight engine operation.

The invention is illustrated by drawings, where:

Fig.1 shows a turbojet engine, a longitudinal section;

Fig.2 - inlet guide vanes KND, top view.

In the method of finishing the turbojet engine is subjected to lapping experienced the engine. TRD is made of double-circuit, double-shaft. Fine-tuning of the engine is produced in stages, which develop software and algorithms development testing, experienced TRD. At each stage were subjected to the tests according to the specified parameters statistically representative number of, preferably, from one to five copies and carry out condition survey of each tested from the number of copies of the CFR engine. For analysis and assessment of the state if necessary, make a takedown, followed by the possible revision and/or replacements of any of the modules and/or nodes of the CFR engine. Inspect and if necessary replace the modified damaged in any of the tests or nesootvetstvie�protocols required parameters module.

TRD contains at least eight modules from the compressor 1 low pressure until fully variable jet nozzle 2. KND includes inlet guide vanes 3 and the rotor shaft 4, which is preferably not more than four working wheels 5 with the blades 6. VNA contains 3 radial power rack 7 consisting of a fixed hollow and managed rolling elements. Radial racks 7 are evenly spaced in the plane of the inlet section with an angular frequency of placement of racks in range (3,0÷4,0) u/rad.

The gasifier includes assemblies, namely the intermediate casing 8, a compressor 9 high pressure main combustion chamber 10 and the turbine 11 high pressure. For the gas generator are sequentially and coaxially installed 12 turbine low pressure, the mixer 13, the front device 14, afterburner chamber 15 of combustion and United with afterburner chamber 15 of combustion variable jet nozzle 2. Above the main combustion chamber 10 in the external circuit TRD module is installed in the air-air heat exchanger 16 and, if necessary, examining any no less than sixty tubular block-modules last.

In addition, inspect and make the necessary fine-tuning gear boxes of motor units (not shown) and combining these modules electric, �pnevmaticheskoy, hydraulic fuel and oil systems, including, if necessary, replacement of sensors, command blocks, actuators and cables systems diagnostics and automatic engine control.

In the test program with the subsequent development of the revision include a test engine to determine the influence of climatic conditions (UWC) on change in performance experienced TRD. For this test, not less than one, for representativeness, preferably, three to five experienced engine. The testing of the prototype engine is carried out on various modes of parameters. The parameters correspond to the parameters of the flight modes in the range programmed for a particular series of engines. Make measurements and perform the conversion of the received parameter values to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the turbojet engine when changing atmospheric conditions. In this pre-create a mathematical model of the turbojet engine. Adjust the model according to the results of bench tests of a representative number of three to five identical TRD. Then a mathematical model is used to determine the parameters of the TRD at standard atmospheric conditions and different tempo�off-highway vehicles used atmospheric air from a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes. The actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of. The conversion of the measured parameters to standard atmospheric conditions is carried out by multiplying the measured values by the factors, taking into account the deviation of the atmospheric pressure from the standard, and correction factor. The correction factor reflects the dependence of the measured values from the temperature of the atmospheric air, registered in the particular test turbojet engines.

Random tests carried out with TRD measuring performance parameters in different modes, the parameters of which correspond in magnitude and limit values of parameters of the flight modes in the range programmed for a particular series of engines. Carry out the conversion of the obtained parameters to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the engine when changing atmospheric conditions. Also in this pre-create a mathematical model of the engine and adjust it according to the results of bench tests of representative�th number from three to five engines. According to the mathematical model to determine the parameters of the engine at standard atmospheric conditions and different temperatures of atmospheric air from a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes. The actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of. The conversion of the measured parameters to standard atmospheric conditions is carried out by multiplying the measured values by the factors, taking into account the deviation of the atmospheric pressure from the standard, and correction factor reflecting the temperature dependence of atmospheric air, registered in the particular test. Taking into account the obtained data, perform the following test cycle with the loading of the engine, which measure the change in the parameters.

Fine-tuning is subjected to an experienced engine, VNA 3 KND 1 which contains, preferably, twenty-three radial strut 7, connecting the inner and outer rings 17 and 18, respectively, VNA 3 capable of transmitting loads from external�corps 19 of the engine on the front support. At least part of the uprights 7 are combined with the oil channels of the system, placed in a stationary element of the racks, with the possibility of supplying and discharging the oil, and venting of oil and premerlani cavities front bearing of the rotor KND.

Fine-tuning is subjected to experimental turbojet, the area of the frontal projection of the input aperture of FBX. Ave, BHA 3 KND 1 which geometrically defines the cross section of the inlet mouth of the intake channel 20, limited to the larger radius of the inner contour of the outer ring 17 VNA 3, and on a smaller radius of the inner contour of the inner ring 18 VNA is made greater than the total area of the aerodynamic shadow FStcreated a front projection 21 and Coca radial struts 7 in (2,54÷2,72) times and is (0,67÷0,77) on the full area of the circle FPLN.that is limited to a radius of the inner contour of the outer ring 17 of the VNA in the plane of the input aperture.

An example implementation of the testing of the prototype turbojet engine.

The test is subjected to a representative group of three to five turbojets. Using a previously developed mathematical model of the engine. Tests specified group TRD carried out at a temperature tI=0°C, Ba=745 mm Hg.PT.

According to the results of measurements and their statistical generalizations get the values of the parameters: the efforts of thedigitel R=985 kgf and a rotational speed n=98,8%.

For subsequent evaluation of the test results using the mathematical model of the engine, at which carry out the calculation of the parameters for different modes of engine operation in the temperature range of the air inlet to the engine, including at tI=+15°C. the results of the calculation are presented in Table.1

Table 1
tI, °C-150+15+30
The temperature at the inlet (TRD
R, kgf1000980970950
Pull force
n, %9899100100
Speed

Compare the above data and calculate correction factors by the relation of the parameter value at tI=+15°C to the parameter values in a predetermined temperature range at the inlet of the engine� (PL.2)

Table 2
tI, °C-15±0+15+30
KR0,970,9911,021
Kn1,021,0111

Then define the parameters under standard atmospheric conditions (ISA)

RMCA=R×KR×760Ba=985×0,99×760745=995KgC,

nMCA=n×Kn=98,8×1,01=97,79%

and make the data in the accompanying documentation to the relevant group TRD.

Using the parameters obtained above TRD to calculate the relevant parameters in relation to temperature and climatic conditions of specific areas of operation of the engines in the range t�of Imperator outdoor air t I=±50°C. Extreme for the specified temperature range parameter values TRD derived from test results using mathematical models and data under standard atmospheric conditions (ISA), presented in Table.3 and Table.4.

Table 3
tI, °C-50-150+15+20+50
The temperature at the inlet (TRD
R, kgf12001000980970950900
The force from thrust
n, %969899100100100
speed

Table 4
tI, °C-50-150+15+20+50
KR0,810,970,9911,0211,078
Kn1,0421,021,01111

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

Thus, the invention improves the reliability of the results of tests of turbojet engines with account taken of the control programs.

The above sequence of tests TRD used to evaluate the changes of traction for different temperature and climatic conditions and modes of operation of the engine.

1. Method of refining experimental turbojet engine, characterized by the fact that fine-tuning is subjected to an experienced engine made d�unconcerned, shaft, wherein the fine-tuning of the engine is produced in stages, which develop software and algorithms development testing, experienced TRD; at each stage were subjected to the tests according to the specified parameters statistically representative number from one to five copies and carry out condition survey of each tested from the number of instances experienced engine; for the analysis and assessment of the state produce disassembly, followed by the possible revision and/or replacements of any of the modules and/or nodes of the CFR engine, inspect and replace modified any of the damaged or inappropriate tests required parameters module, including the compressor low pressure (CLP) with inlet guide vanes (IGV), which contains a power of the radial rack consisting of a fixed and controlled rolling elements and equally spaced in the plane of the inlet section with an angular frequency of placement of racks in range (3,0÷4,0) u/rad, and a rotor shaft, comprising, preferably, not more than four working wheels with a system of blades; a gas generator including assemblies, an intermediate housing, a high pressure compressor, a main combustion chamber and high pressure turbine; sequentially arranged behind the generator, coaxially �chain low pressure turbine; the mixer; the front device, the afterburner combustion chamber and connected to the afterburner combustion chamber of a variable jet nozzle; and mounted above the combustion chamber in the external circuit module air-to-air exchanger, examining any no less than sixty tubular block-modules of the latter, in addition, examine and produce debugging gear boxes of motor units and combining these modules electrical, pneumatic, hydraulic fuel and oil systems, including replacement of sensors, command blocks, actuators and cables systems diagnostics and automatic control of the engine; and testing program with subsequent refining finishing include tests of the engine to determine the influence of climatic conditions (UWC) on change in performance experienced TRD; for this test, not less than one, for the representativeness of three to five experienced engine; the testing of the prototype engine is carried out in various modes whose parameters correspond to the parameters of the flight modes in the range programmed for a particular series of engines, make measurements and perform the conversion of the received parameter values to standard atmospheric conditions to reflect changes in the properties of the slave�their bodies and geometrical characteristics of the flow part of the turbojet engine when changing atmospheric conditions, in this pre-create a mathematical model of the turbojet engine, adjust it according to the results of bench testing of a representative number of three to five identical turbojet engines, and then according to the mathematical model to determine the parameters of the turbojet engine at standard atmospheric conditions and different temperatures of atmospheric air from a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes, and the actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of, and the conversion of the measured parameters to standard atmospheric conditions is carried out by multiplying the measured values by the factors, taking into account the deviation of the atmospheric pressure from the standard, and the correction coefficient reflecting the dependence of the measured values from the temperature of the atmospheric air, registered in the particular test turbojet engines.

2. Method of refining experimental turbojet engine� according to claim 1, characterized in that the TRD test is carried out with measurement of performance parameters for different modes, the parameters of which correspond in magnitude and limit values of parameters of the flight modes in the range programmed for a particular series of engines, and carry out the conversion of the obtained parameters to standard atmospheric conditions to reflect changes in the properties of the working fluid and the geometric characteristics of the flow part of the engine when changing atmospheric conditions, first create a mathematical model of the engine, adjust it according to the results of bench testing 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 a given operating temperature range of bench tests on account of existing programs to manage the engine at maximum and forced modes, and the actual parameter values at specific temperatures for each mode of the test are referred to the values of the parameters at standard atmospheric conditions and calculate correction factors to the measured parameters depending on the atmospheric temperature of, as a conversion of the measured parameters�ditch to standard atmospheric conditions is carried out by multiplying the measured values on the coefficients, taking into account the deviation of the atmospheric pressure from the standard, and correction factor reflecting the temperature dependence of atmospheric air, registered in the particular test, and taking into account the obtained data, perform the following test cycle with the loading of the engine, which measure the change in the parameters.

3. Method of refining experimental turbojet engine according to claim 1, characterized in that the fine-tuning is subjected to an experienced engine, VNA KND of which contains twenty-three radial strut connecting the inner and outer rings VNA capable of transmitting loads from the outside of the motor housing on the front support, and some racks aligned with the channels of the oil system, placed in a stationary element of the racks, with the possibility of supplying and discharging the oil, and venting of oil and premerlani cavities front bearing of the rotor KND.

4. Method of refining experimental turbojet engine according to claim 3, characterized in that the fine-tuning subjected to experimental turbojet, the area of the frontal projection of the input aperture of FBX.PR., BHA KND which geometrically defines the cross section of the inlet mouth of the intake canal, bounded on the larger radius of the inner contour of the outer ring VNA, and the smaller radius of the inner contour of the inner ring of BHA is made greater than the total area of the aerodynamic shadow F Stcreated a front projection Coca and radial struts (2,54÷2,72) times and is (0,67÷0,77) on the full area of the circle FPLN.that is limited to a radius of the inner contour of the outer ring VNA in the plane of the input aperture.



 

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14 cl

FIELD: test equipment.

SUBSTANCE: to shift parameter operating point of a compressor stage to the limits of stable operation, work medium (air) is fed to blade channel of stator in the compressor stage under test. Work medium is fed directly to the blade channel of the tested stage by jet nozzle with diagonal cut. Work medium flow rate is controlled by throttle gate. Work medium can also be fed into hollow stator blade of the tested stage and enter flow section through a special orifice system at the profile surface, causing separation of boundary level.

EFFECT: study of parameters in single stages of axial compressor in turbine engine, study of axial compressor stage operation modes at the limits of stable operation without adverse effect on elements of the engine under test.

3 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: tests of steam and gas turbines of power and propulsion systems at independent test benches is an effective method for advanced testing of new technical solutions which allows for the reduction of the scope, cost and total time needed for new power installation development. The method is implemented with the help of a test bench comprising the turbine being tested with a working medium supply system, a hydraulic brake with working fluid supplying and withdrawing pipelines including, according to the invention, a tank with a system for filling by the working fluid, suction and discharge mains of a fluid loading pump with a system of sensors built-in in them with the sensors being calibrated as per the capacity parameters of the turbine being tested. A throttling device and/or a set of throttling devices is installed in the discharge mains, the fluid loading pump with its shaft being kinematically coupled with the tested turbine is used as the hydraulic brake. The working fluid is supplied to the fluid loading pump in the closed circuit and can be partially withdrawn and supplied to the circuit during the tests.

EFFECT: no necessity to withdraw the working fluid used-up in the hydraulic brake during tests, decreased routine maintenance interval for hydraulic brake, provision for the possibility to change the characteristics of the tested turbine in the wide range during testing.

6 cl, 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.

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