CN118030210A - Scroll engine with stress application based on carbon dioxide thermal management - Google Patents
Scroll engine with stress application based on carbon dioxide thermal management Download PDFInfo
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- CN118030210A CN118030210A CN202410262443.1A CN202410262443A CN118030210A CN 118030210 A CN118030210 A CN 118030210A CN 202410262443 A CN202410262443 A CN 202410262443A CN 118030210 A CN118030210 A CN 118030210A
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- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 title claims abstract description 538
- 229910002092 carbon dioxide Inorganic materials 0.000 title claims abstract description 269
- 239000001569 carbon dioxide Substances 0.000 title claims abstract description 269
- 238000002347 injection Methods 0.000 claims description 19
- 239000007924 injection Substances 0.000 claims description 19
- 238000010438 heat treatment Methods 0.000 claims description 10
- 239000002918 waste heat Substances 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 230000009347 mechanical transmission Effects 0.000 abstract description 3
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 206010063385 Intellectualisation Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention belongs to the technical field of aeroengines, and discloses a turboshaft engine with stress application based on carbon dioxide thermal management, which comprises a turboshaft engine body and a carbon dioxide thermal management system, wherein the carbon dioxide thermal management system comprises a high-pressure carbon dioxide storage tank, a carbon dioxide power component, a carbon dioxide cooler and a carbon dioxide heat exchanger; the aeroengine provided by the invention has the functions of accessory electrification control, electric starting, high electric power output, instantaneous or short-time output shaft power increase and the like, and the engine output shaft power is greatly increased when the aircraft needs. The accessory system and the starting system of the turboshaft engine body are driven by power supply and electric power, a mechanical transmission system is omitted, the accessory and starting efficiency and control precision are improved, meanwhile, the complexity and weight of the engine accessory are reduced, and the structural efficiency and working performance of the accessory are further optimized.
Description
Technical Field
The invention belongs to the technical field of aeroengines, and particularly relates to a turboshaft engine with stress application based on carbon dioxide thermal management.
Background
At present, rotorcraft is rapidly developed towards the directions of intellectualization, unmanned, multifunction and full-regional, and then requirements of high electric power output, wide-range output shaft power, high efficiency and the like are provided for a turboshaft engine of a power device.
The structure of the existing aviation turboshaft engine is shown in fig. 1, and the existing aviation turboshaft engine consists of an air inlet casing 1, an air compressor 2, a combustion chamber 3, a core turbine 4, a power turbine 6, an exhaust casing 7, a shaft power output interface 8 and the like; the functions of each component are as follows: the air inlet casing 1 has the functions of removing sand to ensure that the air inlet of the engine is clean, heating the bleed air and preventing the air inlet from icing, and the air compressor 2 has the function of increasing the air flow pressure of the engine and provides bleed air for the air inlet casing 1 for anti-icing, ventilation and heat insulation of a bearing cavity, cooling of a hot end casing and the like; the combustion chamber 3 has a function of combusting fuel oil in a high-pressure air flow to form fuel gas as a functional power; the core turbine 4 has the function of extracting energy in the fuel gas to form shaft power so as to drive the compressor to compress air flow; the power turbine 6 also has the function of extracting the residual energy in the fuel gas to form shaft power and outputting the shaft power to the outside through the shaft power output interface 8; the exhaust casing 7 is used to guide the gas after the power turbine 6 out of the engine.
The thermodynamic cycle efficiency of the existing aviation scroll engine is close to the limit, and the efficiency gain is not great but the cost is high by continuously optimizing the traditional components; secondly, the traditional aviation turboshaft engine has limited shaft power output range, and the military/civil rotor craft with the traditional aviation turboshaft engine has poor capability or capability of being used in all regions and all climatic conditions; finally, traditional aviation scroll electric power output is limited, the electricity demand of the future highly intelligent aircraft cannot be met, and a mechanical accessory transmission system of the engine is too complex and heavy. Therefore, in order to meet the power requirements of future rotorcraft, the need for innovative development of aviation turboshaft engines is urgent.
Disclosure of Invention
Aiming at the problems, the invention provides a scroll engine with stress application based on carbon dioxide thermal management, which adopts the following technical scheme:
the utility model provides a take afterburning turboshaft engine based on carbon dioxide thermal management, includes turboshaft engine body and carbon dioxide thermal management system, wherein, carbon dioxide thermal management system includes:
The high-pressure carbon dioxide storage tank is used for conveying high-pressure carbon dioxide medium to the carbon dioxide injection device when the external output power of the turboshaft engine body needs to be increased; the carbon dioxide injection device is arranged in a flow passage of a turbine interstage casing of the turboshaft engine body;
The carbon dioxide power component is used for converting the heat energy of the heated high-pressure carbon dioxide medium into mechanical energy, and doing work or generating power outwards; the carbon dioxide power component is also used for conveying the low-pressure carbon dioxide medium with the waste heat discharged after acting to the carbon dioxide cooler;
the carbon dioxide cooler is used for heating and anti-icing the air inlet casing of the turboshaft engine body through the input low-pressure carbon dioxide medium with waste heat and conveying the cooled low-temperature low-pressure carbon dioxide medium to the carbon dioxide power component;
The carbon dioxide power component is also used for compressing the low-temperature low-pressure carbon dioxide medium into a low-temperature high-pressure carbon dioxide medium and conveying the low-temperature high-pressure carbon dioxide medium to the carbon dioxide heat exchanger;
The carbon dioxide heat exchanger is used for heating the low-temperature high-pressure carbon dioxide medium by absorbing heat on the heating part of the turboshaft engine body, and conveying the heated high-temperature high-pressure carbon dioxide medium to the carbon dioxide power component to drive the carbon dioxide power component to do work to generate electric energy.
Further, the high-pressure carbon dioxide storage tank is arranged on the aircraft.
Further, the carbon dioxide power component is arranged outside the compressor casing of the turboshaft engine body.
Further, the carbon dioxide cooler is arranged on the air inlet casing of the turboshaft engine body.
Further, the carbon dioxide heat exchanger is arranged on a turbine interstage casing and an exhaust casing of the turboshaft engine body.
Further, the carbon dioxide heat exchanger comprises a plurality of heat exchange units in a split mode, and at least one heat exchange unit is arranged on the outer side wall of the turbine interstage casing of the turboshaft engine body, the rear bearing cavity in the turbine interstage casing and the side wall of the exhaust casing.
Further, the carbon dioxide power component comprises a generator, a transmission shaft, a compressor and a turbine;
the high-pressure carbon dioxide storage tank is used for conveying a high-pressure carbon dioxide medium to the carbon dioxide thermal management system;
The turbine is used for driving the generator to generate electric energy through the transmission shaft and driving the compressor;
the generator is used for conveying the generated electric energy to a power supply for storage;
the turbine is also used for conveying the high-temperature low-pressure carbon dioxide medium discharged after acting to the carbon dioxide cooler;
the carbon dioxide cooler is used for conveying the cooled low-temperature low-pressure carbon dioxide medium to the compressor for compression;
the compressor is used for compressing the low-temperature low-pressure carbon dioxide medium into the low-temperature high-pressure carbon dioxide medium and conveying the low-temperature high-pressure carbon dioxide medium to the carbon dioxide heat exchanger.
Further, the carbon dioxide heat management system further comprises a three-way valve, a first one-way valve and a first valve;
The first end of the three-way valve is communicated with the high-pressure carbon dioxide storage tank through a pipeline A, the second end of the three-way valve is communicated with the carbon dioxide injection device through a pipeline B, the third end of the three-way valve is communicated with one end of the first one-way valve through a pipeline C, the other end of the first one-way valve is communicated with one end of the first valve through a pipeline D, and the other end of the first valve is communicated with an air inlet of the turbine through a pipeline E.
Further, the carbon dioxide thermal management system also comprises a second one-way valve and a second valve;
The air outlet of the turbine is communicated with the inlet of the carbon dioxide cooler, the outlet of the carbon dioxide cooler is communicated with the air inlet of the compressor, the air outlet of the compressor is communicated with the pipeline B through a pipeline F, the second valve is arranged on the pipeline F, the air outlet of the compressor is further communicated with the pipeline D through a pipeline G, the second one-way valve is arranged on the pipeline G, the pipeline D is further communicated with the inlet of the carbon dioxide heat exchanger through a pipeline H, and the outlet of the carbon dioxide heat exchanger is communicated with the pipeline E through a pipeline I.
Further, the carbon dioxide thermal management system further comprises a third valve, wherein one end of a pipeline J is communicated with the pipeline I, the other end of the pipeline J is communicated with the pipeline B, and the third valve is arranged on the pipeline J.
Further, the carbon dioxide thermal management system further comprises a control unit;
the control unit is used for controlling the opening degrees of the three-way valve, the first valve, the second valve and the third valve.
Further, the control unit is configured to open the third end of the three-way valve if the flow and the pressure of the carbon dioxide working medium at the inlet of the carbon dioxide heat exchanger do not reach the set values, and the high-pressure carbon dioxide storage tank sequentially passes through the pipeline a, the three-way valve, the pipeline C, the pipeline D and the pipeline H to inject the carbon dioxide working medium into the inlet of the carbon dioxide heat exchanger.
Further, the control unit is configured to open the third valve if the pressure of the carbon dioxide working medium at the inlet of the turbine exceeds a set value, and convey the high-temperature and high-pressure carbon dioxide working medium to the carbon dioxide injection device for discharge through a pipeline J and a pipeline B;
If the pressure of the carbon dioxide working medium at the inlet of the turbine does not reach a set value, the first valve is opened, and the high-pressure carbon dioxide storage tank sequentially injects the carbon dioxide working medium into the inlet of the turbine through the pipeline A, the three-way valve, the pipeline C, the pipeline D and the pipeline E.
Further, the control unit is configured to:
if the flow and pressure of the carbon dioxide working medium at the outlet of the compressor exceed the set values, opening the second valve on the pipeline F, and conveying part of the carbon dioxide working medium to the carbon dioxide injection device through the pipeline F and the pipeline B to be discharged.
The invention has the beneficial effects that:
1. The aeroengine provided by the invention has the functions of accessory electrification control, electric starting, high electric power output, instantaneous or short-time output shaft power increase and the like, and the engine output shaft power is greatly increased when the aircraft needs.
2. The accessory system and the starting system of the turboshaft engine body are driven by power supply and electric power, a mechanical transmission system is omitted, the accessory and starting efficiency and control precision are improved, meanwhile, the complexity and weight of the engine accessory are reduced, and the structural efficiency and working performance of the accessory are further optimized.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 shows a schematic structural view of a turboshaft engine according to the prior art;
FIG. 2 shows a schematic diagram of a forced turboshaft engine based on carbon dioxide thermal management in accordance with an embodiment of the present invention;
Fig. 3 shows a schematic structural diagram of a carbon dioxide thermal management system according to an embodiment of the present invention.
In the figure: 1. an air inlet casing; 2. a compressor; 3. a combustion chamber; 4. a core turbine; 5. turbine interstage casing; 6. a power turbine; 7. an exhaust casing; 8. a shaft power output interface; 9. a rear bearing cavity; 10. a high pressure carbon dioxide storage tank; 11. a carbon dioxide power component; 12. a carbon dioxide injection device; 13. a carbon dioxide cooler; 14. a carbon dioxide heat exchanger; 15. a generator; 16. a transmission shaft; 17. a compressor; 18. a turbine; 19. a control unit; 20. a three-way valve; 21. a first one-way valve; 22. a first valve; 23. a second one-way valve; 24. a second valve; 25. a third valve; 26. a pipeline A; 27. a pipeline B; 28. a pipeline C; 29. a pipeline D; 30. a pipeline E; 31. a pipeline F; 32. a pipeline G; 33. a pipeline H; 34. a pipeline I; 35. pipeline J.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that the terms "first," "second," and the like herein are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe the embodiments of the application herein. In the present application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate an azimuth or a positional relationship based on that shown in the drawings.
The invention provides a turboshaft engine with stress application based on carbon dioxide thermal management, which has the functions of accessory electrification control, electric starting, high electric power output, instantaneous or short-time output shaft power increase and the like, and greatly increases the output shaft power of the engine when an aircraft needs.
As shown in FIG. 2, the scroll engine with stress application based on carbon dioxide thermal management comprises a scroll engine body and a carbon dioxide thermal management system.
The turboshaft engine body comprises an air inlet casing 1, a compressor casing, a compressor 2, a combustion chamber 3, a core turbine 4, a turbine interstage casing 5, a power turbine 6 and an exhaust casing 7, wherein the power turbine 6 outputs shaft power to the outside through a shaft power output interface 8, and it is noted that each part of the turboshaft engine body is not an important point of improvement of the invention, and specific functions of each part are not repeated.
As shown in fig. 2 and 3, the carbon dioxide thermal management system includes, among other things, a high-pressure carbon dioxide storage tank 10, a carbon dioxide power component 11, a carbon dioxide injection device 12, a carbon dioxide cooler 13, and a carbon dioxide heat exchanger 14.
For example, the high-pressure carbon dioxide storage tank 10 is disposed on the aircraft, the high-pressure carbon dioxide medium is stored in the high-pressure carbon dioxide storage tank 10, the high-pressure carbon dioxide storage tank 10 is used for conveying the high-pressure carbon dioxide medium to the carbon dioxide thermal management system, and the high-pressure carbon dioxide storage tank 10 is further used for conveying the high-pressure carbon dioxide medium to the carbon dioxide injection device 12 when the output power of the shaft power output interface 8 to the outside needs to be increased, wherein the carbon dioxide injection device 12 is disposed in the flow channel of the turbine interstage casing 5.
The carbon dioxide medium in the high-pressure carbon dioxide storage tank 10 is led to the carbon dioxide injection device 12 in the flow channel of the turbine interstage casing 5, and when the engine needs to increase the output shaft power, the carbon dioxide is injected to increase the output shaft power of the power turbine 6; the other path is led to a closed carbon dioxide heat management system to ensure that the heat management of the engine converts sufficient power.
The carbon dioxide power component 11 is arranged outside the compressor casing, the carbon dioxide power component 11 is used for converting the heat energy of the heated high-pressure carbon dioxide medium into mechanical energy, doing work or generating electricity outwards and transmitting the electric energy to the power supply storage of the aircraft, and the power supply is used for supplying power to electric equipment of the aircraft, an accessory system of the turboshaft engine body and a starting motor of the turboshaft engine body.
The carbon dioxide power component 11 is also used for compressing the low-temperature low-pressure carbon dioxide medium into a low-temperature high-pressure carbon dioxide medium and delivering the low-temperature high-pressure carbon dioxide medium to the carbon dioxide heat exchanger 14.
The carbon dioxide power component 11 is also used for converting energy in the high-temperature high-pressure carbon dioxide medium into mechanical energy for output, and conveying the low-pressure carbon dioxide medium with waste heat discharged after acting to the carbon dioxide cooler 13.
The accessory system and the starting system of the turboshaft engine body are driven by power supply and electric power, a mechanical transmission system is omitted, the accessory and starting efficiency and control precision are improved, and meanwhile, the complexity and weight of the engine accessory are reduced.
The carbon dioxide cooler 13 is arranged on the air inlet casing 1, and the carbon dioxide cooler 13 is used for heating and anti-icing the air inlet casing 1 through the input low-pressure carbon dioxide medium with waste heat and conveying the cooled low-temperature low-pressure carbon dioxide medium to the carbon dioxide power component 11.
The carbon dioxide heat exchanger 14 is used for heating the low-temperature high-pressure carbon dioxide medium by absorbing heat on the heating part of the turboshaft engine body, and conveying the heated high-temperature high-pressure carbon dioxide medium to the carbon dioxide power component 11 to drive the carbon dioxide power component 11 to do work to generate electric energy. For example, the carbon dioxide heat exchanger 14 is disposed on the turbine interstage casing 5 and the exhaust casing 7, and the carbon dioxide heat exchanger 14 is configured to heat the low-temperature high-pressure carbon dioxide medium by heat on the turbine interstage casing 5 and the exhaust casing 7, and to convey the heated high-temperature high-pressure carbon dioxide medium to the carbon dioxide power component 11, so as to drive the carbon dioxide power component 11 to perform work to generate electric energy.
For example, the carbon dioxide heat exchanger 14 includes a plurality of heat exchange units in a split type, and at least one heat exchange unit is provided on the outer side wall of the turbine interstage casing 5, the rear bearing chamber 9 in the turbine interstage casing 5, and the side wall of the exhaust casing 7, and the heat exchange units are provided to extract and reuse heat from the high-temperature parts such as the outer side wall of the turbine interstage casing 5, the rear bearing chamber 9 in the turbine interstage casing 5, and the side wall of the exhaust casing 7.
For example, the carbon dioxide power component 11 includes a generator 15, a drive shaft 16, a compressor 17, and a turbine 18, wherein one end of the drive shaft 16 is drivingly connected to the generator 15, and the other end of the drive shaft 16 is drivingly connected to the compressor 17 and the turbine 18.
The turbine 18 is used for driving the generator 15 to generate electric energy through the transmission shaft 16 and is also used for driving the compressor 17; the generator 15 is used for transmitting the generated electric energy to a power supply for storage; the low-pressure carbon dioxide medium with waste heat discharged after the turbine 18 does work is conveyed to the carbon dioxide cooler 13, the carbon dioxide cooler 13 is used for conveying the cooled low-temperature low-pressure carbon dioxide medium to the compressor 17 for compression, the compressor 17 compresses the low-temperature low-pressure carbon dioxide medium into low-temperature high-pressure carbon dioxide medium, and the low-temperature high-pressure carbon dioxide medium is conveyed to the carbon dioxide heat exchanger 14.
The carbon dioxide power component 11 is used for converting the heat energy of the input high-pressure carbon dioxide medium into mechanical energy, and the process of doing work or generating electricity externally specifically comprises the following steps:
The heated high-pressure carbon dioxide medium drives the turbine 18 to rotate so as to drive the generator 15 to generate electric energy; while turbine 18 drives compressor 17 to rotate to boost the low temperature, low pressure carbon dioxide after carbon dioxide cooler 13.
For example, the carbon dioxide thermal management system further comprises a control unit 19, a three-way valve 20, a first one-way valve 21, a first valve 22, a second one-way valve 23, a second valve 24 and a third valve 25.
The control unit 19 is used for controlling the opening degrees of the three-way valve 20, the first valve 22, the second valve 24 and the third valve 25.
For example, the three-way valve 20, the first valve 22, the second valve 24 and the third valve 25 each include a control module and an execution module, and the control unit 19 is in signal communication with the control module of the three-way valve 20, the control module of the first valve 22, the control module of the second valve 24 and the control module of the third valve 25, and the control module signals of the three-way valve 20, the control module of the first valve 22, the control module of the second valve 24 and the control module of the third valve 25 control the execution module of the three-way valve 20, the execution module of the first valve 22, the execution module of the second valve 24 and the execution module of the third valve 25 according to the instruction of the control unit 19, thereby realizing the control of the opening degree of each valve.
For example, a first end of the three-way valve 20 communicates with the high pressure carbon dioxide storage tank 10 via a line A26, a second end of the three-way valve 20 communicates with the carbon dioxide injection device 12 via a line B27, a third end of the three-way valve 20 communicates with one end of the first check valve 21 via a line C28, the other end of the first check valve 21 communicates with one end of the first valve 22 via a line D29, and the other end of the first valve 22 communicates with an air inlet of the turbine 18 via a line E30.
The gas outlet of turbine 18 communicates with the import of carbon dioxide cooler 13, the export of carbon dioxide cooler 13 communicates with the air inlet of compressor 17, the gas outlet of compressor 17 communicates with pipeline B27 through pipeline F31, second valve 24 sets up on pipeline F31, the gas outlet of compressor 17 still communicates with pipeline D29 through pipeline G32, second check valve 23 sets up on pipeline G32, pipeline D29 still communicates with the import of carbon dioxide heat exchanger 14 through pipeline H33, the export of carbon dioxide heat exchanger 14 communicates with pipeline E30 through pipeline I34, one end of pipeline J35 communicates with pipeline I34, the other end of pipeline J35 communicates with pipeline B27, third valve 25 sets up on pipeline J35.
The thermodynamic cycle principle of the closed carbon dioxide heat management system of the invention is as follows:
The low-temperature high-pressure carbon dioxide working medium pressurized by the compressor 17 enters the carbon dioxide heat exchanger 14 through the pipeline G32 and the pipeline H33 to be heated, and the control unit 19 is used for opening the third end of the three-way valve 20 if the flow and the pressure of the carbon dioxide working medium at the inlet of the carbon dioxide heat exchanger 14 do not reach the set values, and the high-pressure carbon dioxide storage tank 10 sequentially injects the carbon dioxide working medium into the inlet of the carbon dioxide heat exchanger 14 through the pipeline A26, the three-way valve 20, the pipeline C28, the pipeline D and the pipeline H33 to ensure the normal operation of the carbon dioxide heat management system.
The high-temperature high-pressure carbon dioxide working medium heated by the carbon dioxide heat exchanger 14 sequentially enters the turbine 18 through the pipeline I34 and the pipeline E30 to push the turbine 18 to do work.
And the control unit 19 is used for opening the third valve 25 if the pressure of the carbon dioxide working medium at the inlet of the turbine 18 exceeds a set value, and conveying the high-temperature and high-pressure carbon dioxide working medium to the carbon dioxide injection device 12 for discharge through the pipeline J35 and the pipeline B27 so as to maintain the stable operation of the turbine 18.
And the control unit 19 is configured to open the first valve 22 if the pressure of the carbon dioxide working medium at the inlet of the turbine 18 does not reach the set value, and the high-pressure carbon dioxide storage tank 10 sequentially injects the carbon dioxide working medium into the inlet of the turbine 18 through the pipeline a26, the three-way valve 20, the pipeline C28, the pipeline D29 and the pipeline E30 to maintain the turbine 18 to stably operate.
The outlet of the turbine 18 still has a certain temperature (with waste heat) pressure carbon dioxide working medium and flows into the carbon dioxide cooler 13, the carbon dioxide cooler 13 heats and anti-icing the air inlet casing 1 through the input low-pressure carbon dioxide medium with waste heat, the cooled low-temperature low-pressure carbon dioxide medium is conveyed to the compressor 17 to be pressurized, and the pressurized low-temperature high-pressure carbon dioxide medium enters the carbon dioxide heat exchanger 14 again through the pipeline G32 and the pipeline H33 to be heated and enters the next thermodynamic cycle.
And the control unit 19 is used for opening the second valve 24 on the pipeline F if the flow and the pressure of the carbon dioxide working medium at the outlet of the compressor 17 exceed the set values, and conveying part of the carbon dioxide working medium to the carbon dioxide injection device 12 through the pipeline F and the pipeline B for discharge.
The turboshaft engine with the stress application based on carbon dioxide thermal management has the advantages of less air entraining, accessory electrification control, electric starting, high electric power output, instantaneous or short-time increase of output shaft power and the like, the thermal efficiency of the engine is further improved through carbon dioxide closed circulation, the output shaft power of the engine is increased when required through a carbon dioxide injection device 12 arranged in an inter-stage flow passage of a turbine 18, and the structural efficiency and the working performance of accessories are further optimized through an electric driving accessory system and a starting system.
Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (14)
1. The utility model provides a take afterburning turboshaft engine based on carbon dioxide thermal management, its characterized in that includes turboshaft engine body and carbon dioxide thermal management system, wherein, carbon dioxide thermal management system includes:
The high-pressure carbon dioxide storage tank is used for conveying high-pressure carbon dioxide medium to the carbon dioxide injection device when the external output power of the turboshaft engine body needs to be increased; the carbon dioxide injection device is arranged in a flow passage of a turbine interstage casing of the turboshaft engine body;
The carbon dioxide power component is used for converting the heat energy of the heated high-pressure carbon dioxide medium into mechanical energy, and doing work or generating power outwards; the carbon dioxide power component is also used for conveying the low-pressure carbon dioxide medium with the waste heat discharged after acting to the carbon dioxide cooler;
the carbon dioxide cooler is used for heating and anti-icing the air inlet casing of the turboshaft engine body through the input low-pressure carbon dioxide medium with waste heat and conveying the cooled low-temperature low-pressure carbon dioxide medium to the carbon dioxide power component;
The carbon dioxide power component is also used for compressing the low-temperature low-pressure carbon dioxide medium into a low-temperature high-pressure carbon dioxide medium and conveying the low-temperature high-pressure carbon dioxide medium to the carbon dioxide heat exchanger;
The carbon dioxide heat exchanger is used for heating the low-temperature high-pressure carbon dioxide medium by absorbing heat on the heating part of the turboshaft engine body, and conveying the heated high-temperature high-pressure carbon dioxide medium to the carbon dioxide power component to drive the carbon dioxide power component to do work to generate electric energy.
2. The carbon dioxide thermal management-based forced turboshaft engine of claim 1 wherein the high pressure carbon dioxide storage tank is disposed on an aircraft.
3. The carbon dioxide thermal management-based forced turboshaft engine of claim 1 wherein the carbon dioxide power component is disposed external to a compressor case of the turboshaft engine block.
4. The carbon dioxide thermal management-based forced turboshaft engine of claim 1 wherein the carbon dioxide cooler is disposed on an intake casing of the turboshaft engine block.
5. The carbon dioxide thermal management-based forced turboshaft engine of claim 1 wherein the carbon dioxide heat exchanger is disposed on a turbine interstage casing and an exhaust casing of the turboshaft engine block.
6. The scroll engine with stress application based on carbon dioxide thermal management according to claim 5, wherein the carbon dioxide heat exchanger is split and comprises a plurality of heat exchange units, and at least one heat exchange unit is arranged on the outer side wall of a turbine interstage casing of the scroll engine body, a rear bearing cavity in the turbine interstage casing and the side wall of an exhaust casing.
7. The carbon dioxide thermal management-based forced turboshaft engine of any one of claims 1-6 wherein the carbon dioxide power components include a generator, a drive shaft, a compressor, and a turbine;
the high-pressure carbon dioxide storage tank is used for conveying a high-pressure carbon dioxide medium to the carbon dioxide thermal management system;
The turbine is used for driving the generator to generate electric energy through the transmission shaft and driving the compressor;
the generator is used for conveying the generated electric energy to a power supply for storage;
the turbine is also used for conveying the high-temperature low-pressure carbon dioxide medium discharged after acting to the carbon dioxide cooler;
the carbon dioxide cooler is used for conveying the cooled low-temperature low-pressure carbon dioxide medium to the compressor for compression;
the compressor is used for compressing the low-temperature low-pressure carbon dioxide medium into the low-temperature high-pressure carbon dioxide medium and conveying the low-temperature high-pressure carbon dioxide medium to the carbon dioxide heat exchanger.
8. The carbon dioxide thermal management-based forced turboshaft engine of claim 7 wherein the carbon dioxide thermal management system further comprises a three-way valve, a first one-way valve, and a first valve;
The first end of the three-way valve is communicated with the high-pressure carbon dioxide storage tank through a pipeline A, the second end of the three-way valve is communicated with the carbon dioxide injection device through a pipeline B, the third end of the three-way valve is communicated with one end of the first one-way valve through a pipeline C, the other end of the first one-way valve is communicated with one end of the first valve through a pipeline D, and the other end of the first valve is communicated with an air inlet of the turbine through a pipeline E.
9. The carbon dioxide thermal management-based forced turboshaft engine of claim 8 wherein the carbon dioxide thermal management system further comprises a second check valve and a second valve;
The air outlet of the turbine is communicated with the inlet of the carbon dioxide cooler, the outlet of the carbon dioxide cooler is communicated with the air inlet of the compressor, the air outlet of the compressor is communicated with the pipeline B through a pipeline F, the second valve is arranged on the pipeline F, the air outlet of the compressor is further communicated with the pipeline D through a pipeline G, the second one-way valve is arranged on the pipeline G, the pipeline D is further communicated with the inlet of the carbon dioxide heat exchanger through a pipeline H, and the outlet of the carbon dioxide heat exchanger is communicated with the pipeline E through a pipeline I.
10. The carbon dioxide thermal management-based forced turboshaft engine of claim 9 wherein the carbon dioxide thermal management system further comprises a third valve, wherein one end of line J communicates with line I and the other end of line J communicates with line B, the third valve being disposed on line J.
11. The carbon dioxide thermal management-based forced turboshaft engine of claim 10 wherein the carbon dioxide thermal management system further comprises a control unit;
the control unit is used for controlling the opening degrees of the three-way valve, the first valve, the second valve and the third valve.
12. The scroll engine with stress application based on carbon dioxide thermal management according to claim 11, wherein the control unit is configured to open the third end of the three-way valve if the flow rate and pressure of the carbon dioxide working medium at the inlet of the carbon dioxide heat exchanger do not reach the set values, and the high-pressure carbon dioxide storage tank sequentially injects the carbon dioxide working medium into the inlet of the carbon dioxide heat exchanger through a pipeline a, a three-way valve, a pipeline C, a pipeline D and a pipeline H.
13. The scroll engine with stress application based on carbon dioxide thermal management according to claim 11, wherein the control unit is configured to open the third valve if the pressure of the carbon dioxide working medium at the inlet of the turbine exceeds a set value, and to deliver the high-temperature and high-pressure carbon dioxide working medium to the carbon dioxide injection device for discharge through a pipeline J and a pipeline B;
If the pressure of the carbon dioxide working medium at the inlet of the turbine does not reach a set value, the first valve is opened, and the high-pressure carbon dioxide storage tank sequentially injects the carbon dioxide working medium into the inlet of the turbine through the pipeline A, the three-way valve, the pipeline C, the pipeline D and the pipeline E.
14. The carbon dioxide thermal management-based forced turboshaft engine of claim 11 wherein the control unit is configured to:
if the flow and pressure of the carbon dioxide working medium at the outlet of the compressor exceed the set values, opening the second valve on the pipeline F, and conveying part of the carbon dioxide working medium to the carbon dioxide injection device through the pipeline F and the pipeline B to be discharged.
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| CN202410262443.1A CN118030210A (en) | 2024-03-07 | 2024-03-07 | Scroll engine with stress application based on carbon dioxide thermal management |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410262443.1A CN118030210A (en) | 2024-03-07 | 2024-03-07 | Scroll engine with stress application based on carbon dioxide thermal management |
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