Method and system for determining refrigerant cooling flow parameter

FIELD: power industry.

SUBSTANCE: method may include receiving a signal associated with the first combustion product parameter value at a specific location within a gas turbine combustion zone, reception of a signal associated with the second combustion product parameter value at a specific location downstream below a combustion zone, comparing the first and the second combustion product parameter values and refrigerant cooling flow parameter determination through comparison of the first and second values.

EFFECT: improved efficiency and improved performance of gas turbine.

20 cl, 3 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: anti-icing system of the gas turbine engine contains the heat exchanger installed in air-gas channel of the engine upstream the engine compressor. The air tapped downstream the last stage of the compressor is supplied through the heat exchanger into the turbine cooling system. The pressure ratio of the compressor is greater than 25, and flow rate of the air tapped from the compressor amounts δ = (0.05÷0.07)·(1+m), where δ - a share of the air tapped from the compressor; m - engine bypass ratio. Between the heat exchanger and the compressor the protection grid is installed.

EFFECT: anti-icing system protects the engine from penetration of ice and other foreign subjects, improves traction and input-output characteristics of the engine.

4 cl, 2 dwg

Gas-turbine engine // 2553919

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine includes at least one cooled turbine stage with a nozzle diaphragm with blades above it and under it, turbine rotor and stator cooling systems, a turbine housing and a radial clearance control system. The turbine housing consists of an external housing and an internal cover with at least one annular insert installed between them. Rotor and stator cooling systems of each turbine stage are independent and contain cooling air extraction lines and flow rate controls, but all the cooling air extraction lines are connected to a cavity after a compressor. The gas-turbine engine can contain an onboard computer and radial clearance measuring sensors above each impeller of all the cooled turbine stages, which are connected with electrical communications to the onboard computer. Each annular insert can be hollow. The internal cavity of each annular insert can be filled with a heat-accumulating substance.

EFFECT: achieving efficient control of radial clearances in the turbine in all modes, increasing engine thrust in takeoff and augmented modes, and improving turbine efficiency and reliability.

4 cl, 6 dwg

FIELD: power industry.

SUBSTANCE: turbine includes first internal wall, second internal wall, internal lining and protective element. First internal wall and second internal wall are mounted on internal lining. First and second internal walls are positioned so as the internal space through which turbine work fluid can flow is separated from external space through which cooling fluid can flow. First and second internal walls and internal lining are positioned against each other so as a cavity is formed in the external space. Protection element is positioned inside the cavity so that the protective element separates the cavity into internal zone and external zone formed in radial external position against the internal zone.

EFFECT: efficient cooling of turbine parts.

9 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: adjustment method of a radial gap in a turbine of a double-flow gas turbine engine involves cooling of a rotor by high pressure air taken from a compressor and of a stator by air of the second circuit. Turbine stator cooling involves some part of air flow rate of the second circuit, which is taken using an air intake, and cooling air velocity in a turbine stator cooling circuit is increased. The radial gap is measured, and depending on its value the cooling air flow rate for turbine stator cooling is changed. The used air is discharged to the second circuit or after the turbine. The double-flow gas turbine engine includes a compressor, a combustion chamber and a cooled turbine. The turbine stator is made so that it is cooled by air of the second circuit. The supply system of stator cooling air is made in the form of an air intake installed in the second circuit and a flow control with a drive, as well as it includes an onboard computer and radial gap measurement sensors. Flow control drive and radial gap measurement sensors are connected through electrical connections to the onboard computer.

EFFECT: achieving effective control of radial gaps in a turbine in all modes; increasing engine thrust in takeoff and boost modes; improving efficiency and reliability of a turbine.

4 cl, 15 dwg

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine (GTE) comprises a compressor, a combustion chamber, a turbine comprising a cooled stage with a nozzle block with cavities above and under it, and a turbine rotor with a cooled impeller and a swirling device upstream it. A turbine stator comprises at least two turbine vessels with cavities between them. The system of radial gap adjustment comprises a circular insert above the turbine impeller. The cavity above the nozzle block is connected with a pipeline of air bleeding, comprising a controller of flow rate with outlet from a compressor. One of cavities between turbine vessels is connected with a pipeline comprising the second controller of flow rate with an intermediate stage of the compressor. The radial gap adjustment system comprises an on-board computer and sensors for radial gap measurement, a flow rate controller, drives of valves and sensors for measurement of the radial gap are connected by electric links. Flow rate of cooling air for turbine rotor cooling is varied depending on the mode of GTE operation, and when the radial gap achieves zero value, the maximum possible flow rate is switched on for cooling of the turbine regardless of the GTE operation mode.

EFFECT: efficient regulation of radial gaps in a turbine at all modes.

4 cl, 16 dwg

FIELD: engines and pumps.

SUBSTANCE: double-flow gas-turbine engine includes a high-pressure compressor, a combustion chamber, a high-pressure turbine with cooled moving blades, and a low-pressure turbine. Dummy cavity of the compressor is separated from a flow part of the compressor with a labyrinth seal. A moving blade cooling line is connected through a swirling unit, inner cavities of nozzle blades of the high- pressure turbine and an air-to-air heat exchanger of the high-pressure turbine to an air cavity of the combustion chamber. The low-pressure turbine is provided with a supercharging line of an inter-disc cavity and with cooling line of its nozzle blades connected to dummy cavity of the compressor through the air-to-air heat exchanger. A cavity adjacent to side surface of the high-pressure turbine disc on the swirling unit side between the shaft and the swirling unit is combined with dummy cavity of the compressor. On the cooling line of high-pressure moving blades there installed is a flow-controlling element. The cooling line of nozzle blades of the low-pressure turbine is separated from the supercharging line of the inter-disc cavity, and its connection to dummy cavity is made through a controlled valve. The air-to-air heat exchanger is made in the form of an air-to-air heat exchanger of the low-pressure turbine and an additional air-to-air heat exchanger, which are installed on the supercharging line of the inter-disc cavity and on the cooling line of nozzle blades of the low-pressure turbine respectively.

EFFECT: reduction of cooling air flow rate for cooling of moving blades of the high- pressure turbine and for cooling of nozzle blades of the low-pressure turbine in modes with partial trip of cooling without deterioration of their cooling reliability; increase in economy of an engine and its efficiency and reduction of specific fuel flow rate in more continuous operating modes.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: power plant (112) includes gas turbine engine (116) fed with fuel through fuel feed circuit (122) passing from tank (124) located on the level of frame (110), and engine cooling circuit (118, 130) containing the first and heat exchanger (120, 132) of the engine to remove calories. Frame (110) includes source (134) of heat emissions. The fuel used to feed gas turbine engine (116) is used as heat carrier fluid medium to dissipate thermal emissions generated on the level of frame (110) on the level of power plant (112). Some amount of the heat transferred with fuel is extracted with heat carrier fluid medium of the engine cooling circuit (118, 130) and is dissipated with the first heat exchanger (120, 132) of the engine so that the temperature of the fuel fed to gas turbine engine (116) can be maintained below a certain threshold value.

EFFECT: improvement of the method.

6 cl, 6 dwg

FIELD: machine building.

SUBSTANCE: proposed device comprises noise-and-heat protection casing to make together with engine housing an annular chamber, set of fans communicated with annular manifold with orifices directed toward gas turbine unit engine cooled surface. Annular manifold orifices are directed so that their axes extend parallel with engine lengthwise axis. Annular waste (hot) air receiver is arranged behind engine cooled surface to communicate with ambient air.

EFFECT: higher efficiency of cooling and engine reliability.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: double-flow gas turbine engine includes compressor with dummies cavity, combustion chamber, high and low pressure turbine, and heat exchanger. The latter is arranged in external circuit, the inlet of which is interconnected with secondary combustion chamber zone, and outlet is interconnected through control valves to air manifold connected to transit cavities of blades of nozzle assembly of high and low pressure turbine. Transit cavities of blades of nozzle assembly of high pressure turbine are interconnected with swirling assembly of high pressure turbine. External circuit is interconnected through rotary guide vane and channels in rotor disc of low pressure turbine with inner cavities of cooled rotating blades of low pressure turbine, the outlet of which is interconnected through openings made on bandage flange behind radial tooth, with blading part of turbine. Some part of inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, is separated with partition from the rest cavity of rotating blade and is interconnected on one side through additional channels in rotor disc of LP turbine, swirling assembly of LP turbine and additional manifold with transit cavity of blades of nozzle assembly of LP turbine, which is arranged on the side of their inlet edges. In each blade of nozzle assembly of LP turbine, the transit cavity is separated with a partition from the rest part of inner cavity and is connected through additional heat exchanger installed in external circuit to dummies cavity of compressor on the other side. Inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, through the openings made on bandage flange of rotating blade of LP turbine before radial tooth is interconnected with blading part of the turbine.

EFFECT: invention increases the installed cooling air pressure drop of LP turbine, which improves the cooling efficiency.

9 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed system comprises radial-flow compressor feeing ring combustion chamber via diffuser, ring compartment arranged axially from diffuser to zone adjoining combustion chamber outlet and diffuser flange rear end. Diffuser ring flange features, in fact, L-like cross-section and is located behind and along radial-flow compressor impeller to form radial annular airflow channel communicated with compressor outlet via its radially outer end. Ring compartment is located radially between combustion chamber and diffuser flange. Note here that said compartment has radially outward ring wall to direct airflow from diffuser along radially inner wall of combustion chamber and radially inner ring wall to constrict ring air passage together with diffuser flange.

EFFECT: better ventilation, higher operating performances of gas turbine engine.

14 cl, 2 dwg

FIELD: gas-turbine engines for aerospace and ground applications.

SUBSTANCE: proposed gas-turbine engine turbocompressor provided with rear support disposed under combustion chamber has two inner air-cooling cavities, first one being disposed in front part of compressor rotor between shafts and second cavity, under first one around turbocompressor rear support between inner and outer flanges; turbocompressor shaft has bypass holes. Air discharge cavity is formed by shells within second inner air-cooling cavity.

EFFECT: enhanced reliability and economic efficiency of engine due to reduced loss in cooling circuit.

2 cl, 1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine contains compressor section for compressing intake air into high-pressure air and intermediate pressure air, combustion chamber section for combustion of fuel with compressed air, communicating with compressor section, turbine section connected with said combustion chamber section for receiving gaseous combustion products from combustion chamber. Turbine section contains turbine blade with head in area of pressure lower than intermediate pressure indicated above. Ring space arranged higher than compressor section in direction of flow and it contains branch for intermediate pressure air. Partition is installed in ring space to transform dynamic head of intermediate pressure air into higher static pressure air. Gas-turbine engine is provided with channel having inlet hole for communicating with space and outlet hole communicating with turbine blade to direct intermediate pressure air at higher pressure to turbine blade, thus cooling the blade.

EFFECT: improved efficiency of cooling of high-pressure turbine.

10 cl, 3 dwg

FIELD: aircraft industry; gas-turbine engines.

SUBSTANCE: invention relates to gas-turbine engine with axis X, having from input of output, high-pressure compressor whose rotor contains outlet fairing 4, diffuser 3, extended at the rear from side of axis X by inner casing arranged radially outside from indicated outlet fairing of compressor, combustion chamber arranged radially outside from said inner casing of diffuser and high-pressure turbine whose rotor is connected with outlet fairing of compressor by mans of coupling. Under chamber space is formed between inner casing of diffuser and outlet fairing of compressor which is located at outlet of unloading labyrinth 13 and in which cooling air circulates from inlet to outlet. Gas-turbine engine contains additionally fairing of stator 20 installed under inner casing of diffuser at outlet of unloading labyrinth 13.

EFFECT: reduced loads in annular space and temperature of cooling air in space.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: three-flow turbo-ejector engine includes inlet device, compressor, the main combustion chamber, turbine, gas ejector. High pressure channel of ejector is connected on one side to compressor through the main combustion chamber, and on the other - to turbine through mixing chamber. Low pressure channel of ejector is connected on one side to atmosphere through the inlet device, and on the other - to turbine through mixing chamber, afterburner, outlet device. Before compressor there installed is fan some portion of air of which is bypassed owing to the last stage to afterburner through the channel (the third channel) located in internal cavities: of compressor, the main combustion chamber, mixing chamber, turbine. At total degree of pressure increase in take off conditions 3.5÷4.0 degree of fan pressure increase is equal to compressor pressure increase degree.

EFFECT: air bypass allows increasing the front thrust and degree of forcing of turbo-ejector engine, as well as improving its cooling.

2 cl, 1 dwg

FIELD: machine building.

SUBSTANCE: device for gas-turbine installation cooling consists of block of fans and of circular collector with orifices directed onto cooled surface of gas-turbine installation. Closed heat resistant elastic cases are assembled on the collector on both sides of a circular zone wherein there are arranged orifices. The said cases can be shaped into a circular circuit of the gas duct when a cooling air flow runs between them. With their free ends they contact cooled surface of the gas-turbine installation (GTI). The invention facilitates direction of whole volume of cooling air into the cooling zone of the gas-turbine installation thus intensifying heat exchange on its cooled surface. The closed heat resistant elastic cases screen heat radiation from hot surface of the gas turbine installation.

EFFECT: reduced consumption of cooling air, of power consumed with fans and of electric power in general.

1 dwg

Gas turbine engine // 2414616

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine includes compressor with add stages with annular bleeding cavity located behind them. Bleeding cavity is connected to air bypass cavity with bypass flaps located in it. From bypass cavity in front of flaps there made is at least one air bleeding channel. Channel is connected by means of pipelines to air blowing cavities of turbine and compressor housings. Surface area of the opening between cavities is less than the surface area of the opening in bypass cavity before flaps by 1.1…2.0 times. Air bleed for blowing of turbine and compressor housings is made at an angle of α=90°…180° from flow direction to air bypass cavities.

EFFECT: invention allows improving reliability and reducing the engine manufacturing cost by controlling radial gaps between stator and rotor.

2 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: turbo-machine consists of unit of diffuser-rectifier (12) set at output of impeller (18) of centrifugal compressor (14) and supplying air into circular combustion chamber (10) and of device (36) of air supply for ventilation of turbine. The unit of the diffuser-rectifier consists of lower circular flange (30) with its lower end connected with devices for supply and together with lower surface (40) of the impeller restricting circular cavity (41) of circulation of air for ventilation withdrawn at an output of the compressor. Device withdrawing part of air volume (92) for ventilation of turbine and device for direction of withdrawn air (83) to radial internal part of lower surface of the impeller are installed on device (36) of supply. Air is circulated radially from inside outside along lower surface of the impeller and is mixed with air withdrawn at output (26) of the compressor for lowering air temperature in circular cavity (41).

EFFECT: raised reliability of machine.

7 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed system of gas turbine engine comprises radial-flow compressor feeding combustion chamber via diffuser, inner casing with, in fact, L-shape cross-section attached to said diffuser to extend along the flow to turbine vent air injection means, and annular sheet element of convection. The latter is arranged in radial direction between combustion chamber and said inner casing to extend axially from said diffuser to said injection means along radially inner wall of combustion chamber to constrict, together with chamber inner wall, the annular air flow channel without airflow separation and with reduced loss in head. Annular channel serves to feed aforesaid openings made in combustion chamber inner wall and air injection means.

EFFECT: higher efficiency.

9 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed system comprises radial-flow compressor feeing ring combustion chamber via diffuser, ring compartment arranged axially from diffuser to zone adjoining combustion chamber outlet and diffuser flange rear end. Diffuser ring flange features, in fact, L-like cross-section and is located behind and along radial-flow compressor impeller to form radial annular airflow channel communicated with compressor outlet via its radially outer end. Ring compartment is located radially between combustion chamber and diffuser flange. Note here that said compartment has radially outward ring wall to direct airflow from diffuser along radially inner wall of combustion chamber and radially inner ring wall to constrict ring air passage together with diffuser flange.

EFFECT: better ventilation, higher operating performances of gas turbine engine.

14 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: double-flow gas turbine engine includes compressor with dummies cavity, combustion chamber, high and low pressure turbine, and heat exchanger. The latter is arranged in external circuit, the inlet of which is interconnected with secondary combustion chamber zone, and outlet is interconnected through control valves to air manifold connected to transit cavities of blades of nozzle assembly of high and low pressure turbine. Transit cavities of blades of nozzle assembly of high pressure turbine are interconnected with swirling assembly of high pressure turbine. External circuit is interconnected through rotary guide vane and channels in rotor disc of low pressure turbine with inner cavities of cooled rotating blades of low pressure turbine, the outlet of which is interconnected through openings made on bandage flange behind radial tooth, with blading part of turbine. Some part of inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, is separated with partition from the rest cavity of rotating blade and is interconnected on one side through additional channels in rotor disc of LP turbine, swirling assembly of LP turbine and additional manifold with transit cavity of blades of nozzle assembly of LP turbine, which is arranged on the side of their inlet edges. In each blade of nozzle assembly of LP turbine, the transit cavity is separated with a partition from the rest part of inner cavity and is connected through additional heat exchanger installed in external circuit to dummies cavity of compressor on the other side. Inner cavity of each rotating blade of LP turbine, which is adjacent to inlet edge, through the openings made on bandage flange of rotating blade of LP turbine before radial tooth is interconnected with blading part of the turbine.

EFFECT: invention increases the installed cooling air pressure drop of LP turbine, which improves the cooling efficiency.

9 cl, 6 dwg

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