CN117052559A - Ram air turbine power generation system with self-precooling function - Google Patents
Ram air turbine power generation system with self-precooling function Download PDFInfo
- Publication number
- CN117052559A CN117052559A CN202311168046.XA CN202311168046A CN117052559A CN 117052559 A CN117052559 A CN 117052559A CN 202311168046 A CN202311168046 A CN 202311168046A CN 117052559 A CN117052559 A CN 117052559A
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- China
- Prior art keywords
- air
- air turbine
- temperature
- ram air
- heat exchanger
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000010248 power generation Methods 0.000 title claims abstract description 16
- 238000001816 cooling Methods 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000005611 electricity Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000000463 material Substances 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
- 239000003921 oil Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
Abstract
The application provides a ram air turbine power generation system with a self-precooling function. The high-temperature high-pressure air in the air inlet channel is communicated with a hot side inlet of the heat exchanger, a hot side outlet of the heat exchanger is communicated with an inlet of the air turbine, and an outlet of the air turbine is communicated with a cold side inlet of the heat exchanger. According to the ram air turbine power generation system with the self-precooling function, high-temperature air flowing in an air inlet channel is precooled through air after the air turbine is expanded and cooled. When the expansion ratio of the ram air turbine is large, the temperature of the ram air after expansion can be controlled to a very low level, so that the ram air turbine is ensured to have a safe and reliable working environment, and the failure or damage caused by the high-temperature environment is avoided.
Description
Technical Field
The application belongs to the technical field of aeroengine thermal management, and particularly relates to a ram air turbine power generation system with a self-precooling function.
Background
With the development of hypersonic technology, higher and higher requirements are put on the wide-range flight performance of the aircraft. In the development of hypersonic aircraft, propulsion power technology is the most critical technical support among them. When the design speed of the aircraft is greater than mach 3, the conventional turbojet or turbofan engine cannot be used as a power source, and the scramjet engine which can work above mach 7 cannot provide enough thrust below mach 3. Therefore, combined engines based on turbine engines and ramjet engines are receiving increasing attention. However, because the ramjet engine has no rotating part, the traditional scheme of driving the generator to generate electricity through the engine rotating shaft cannot be adopted, and therefore, the high-speed incoming flow when the aircraft flies at high speed is utilized to drive the air turbine to perform expansion work so as to generate electricity, so that the method becomes one of the alternative schemes.
However, the stagnation temperature of the incoming air is rapidly increased while the aircraft flies at a high Mach number, the stagnation temperature of the aircraft flies at Mach 6 reaches 1640K, the stagnation temperature of the aircraft flies at Mach 10 reaches 3300K, and the ultrahigh stagnation temperature brings an extremely high thermal load to the air turbine. With the current material's temperature resistance, the highest temperature resistance of an uncooled blade is about 1200K. Therefore, when the total temperature of the incoming flow exceeds 1200K, the turbine blades must be cooled in order to ensure a stable operation of the air turbine power plant for a long period of time. The blade cooling technology adopted by the traditional aeroengine at present mainly comprises modes of impact cooling, air film cooling, turbulent flow cooling and the like, and as the size of the air turbine blade is generally smaller, the air film hole and other structures cannot be processed to realize the cooling of the turbine blade.
Therefore, in order to ensure a safe and reliable working thermal environment for the ram air turbine, pre-cooling of the incoming high temperature air must be achieved. In hypersonic flight, the available heat sink is very stressed, and at present, the bleed air precooling mainly adopts a fuel oil air heat exchanger to realize air cooling. However, the use of a fuel air heat exchanger requires redesigning the fuel supply system to supply sufficient oil to meet the cooling air flow demand, increasing the design difficulty and workload of the engine fuel system. Therefore, it is necessary to find other available heat sinks and design a set of efficient ram air turbine power generation systems with pre-cooling functions.
The present application has been made in view of this.
Disclosure of Invention
The application provides a ram air turbine power generation system with a self-precooling function, which aims to solve the technical problem that the total temperature of an inlet of an air turbine is extremely high during high Mach flight of an aircraft in the background art. In order to solve the technical problems, the application adopts the basic conception of the technical scheme that:
the application provides a ram air turbine power generation system with a self-precooling function, which comprises an air turbine and a heat exchanger.
When the total temperature of the incoming air is larger than a set value, high-temperature and high-pressure air in the air inlet channel is communicated with a hot side inlet of the heat exchanger, a hot side outlet of the heat exchanger is communicated with an inlet of the air turbine, and an outlet of the air turbine is communicated with a cold side inlet of the heat exchanger.
Further, the temperature set point T 1 1200K.
Further, the expansion ratio required for the ram air turbine is designed based on the total temperature of the incoming air outside the aircraft.
Further, the ram air turbine is an axial turbine or a radial turbine.
The ram air turbine power generation system with the self-precooling function provided by the application has the advantages that when the incoming air inlet temperature is greater than the set value T 1 And when the ram air turbine expands and cools, the ram air precools the incoming high-temperature air in the air inlet channel. When the expansion ratio of the ram air turbine is large, the temperature of the expanded ram air can be controlled to be very low, the stream of cold air enters the heat exchanger to realize the precooling of incoming high-temperature air, so that the ram air turbine is ensured to have a safe and reliable working environment, and the failure or damage caused by the high-temperature environment is avoided.
The following describes the embodiments of the present application in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. It is evident that the drawings in the following description are only examples, from which other drawings can be obtained by a person skilled in the art without the inventive effort. In the drawings:
fig. 1 is a ram air turbine power generation system with self-precooling in the practice of the application.
In the figure: 100-air turbine, 200-heat exchanger.
It should be noted that these drawings and the written description are not intended to limit the scope of the inventive concept in any way, but to illustrate the inventive concept to those skilled in the art by referring to the specific embodiments.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions in the embodiments will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present application, and the following embodiments are used to illustrate the present application, but are not intended to limit the scope of the present application.
In the description of the present application, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
Example 1
As shown in fig. 1, in order to solve the technical problem that the total temperature of the inlet of the air turbine is extremely high during high-mach flight of an aircraft, the embodiment provides a ram air turbine power generation system with a self-precooling function, so that the ram air turbine is in a safe and reliable working thermal environment, and deformation and failure of the ram air turbine at high temperature are avoided.
The system includes an air turbine 100, a heat exchanger 200.
When the total temperature of the incoming air inlet is greater than the set value T 1 When the high-temperature high-pressure air in the air inlet channel is communicated with the hot side inlet of the heat exchanger 200, the hot side outlet of the heat exchanger 200 is communicated with the inlet of the air turbine 100, and the outlet of the air turbine 100 is communicated with the cold side inlet of the heat exchanger 200. The high-temperature high-pressure ram air introduced from the air inlet channel firstly enters the heat exchanger 200 to serve as a heat source of the heat exchanger 200, and after being subjected to heat release and temperature reduction in the heat exchanger 200, the ram air enters the air turbine 100 to expand and do work, the low-temperature air after expansion and temperature reduction serves as a cold source of the heat exchanger 200 to cool incoming high-temperature air, and the ram air circulates in such a way, so that the precooling of the incoming high-temperature air by cold air at the outlet of the air turbine 100 is realized, and the air turbine 100 is ensured to be in a reliable temperature range.
Preferably, the temperature set point T 1 1200K.
Preferably, the expansion ratio required for the ram air turbine 100 is designed based on the total temperature of the incoming air outside the aircraft.
Preferably, the ram air turbine 100 is an axial turbine or a radial turbine.
The ram air turbine power generation system with the self-precooling function provided by the application has the advantages that when the total temperature of an incoming air inlet is greater than a set value T 1 In this case, the ram air turbine 100 is expanded and cooled to pre-cool the ram air flowing in the intake duct with high-temperature air. When the ram air turbine 100 is relatively large in expansion, the ram air is post-expansion warmedThe temperature can be controlled to a very low level, and the cold air enters the heat exchanger 200 to realize the precooling of the incoming high-temperature air, so that the ram air turbine 100 is ensured to have a safe and reliable working environment, and the failure or damage caused by the high-temperature environment is avoided.
The foregoing description is only illustrative of the preferred embodiment of the present application, and is not to be construed as limiting the application, but is to be construed as limiting the application to any and all simple modifications, equivalent variations and adaptations of the embodiments described above, which are within the scope of the application, may be made by those skilled in the art without departing from the scope of the application.
Claims (4)
1. The ram air turbine power generation system with the self-precooling function is characterized by comprising an air turbine (100) and a heat exchanger (200), when the total temperature of incoming air is larger than a set value, high-temperature and high-pressure air in the air inlet channel is communicated with a hot side inlet of the heat exchanger (200), a hot side outlet of the heat exchanger (200) is communicated with an inlet of the air turbine (100), and an outlet of the air turbine (100) is communicated with a cold side inlet of the heat exchanger (200).
2. A ram air turbine power generation system with self-precooling function as claimed in claim 1, characterized in that the temperature set point T 1 1200K.
3. A ram air turbine power generation system with self-precooling as claimed in claim 1, characterized in that the expansion ratio required for the ram air turbine (100) is designed in dependence on the total temperature of the incoming air outside the aircraft.
4. A ram air turbine power generation system with self-precooling as claimed in claim 1 wherein the ram air turbine is an axial flow turbine or a radial flow turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311168046.XA CN117052559A (en) | 2023-09-11 | 2023-09-11 | Ram air turbine power generation system with self-precooling function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311168046.XA CN117052559A (en) | 2023-09-11 | 2023-09-11 | Ram air turbine power generation system with self-precooling function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117052559A true CN117052559A (en) | 2023-11-14 |
Family
ID=88657270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311168046.XA Pending CN117052559A (en) | 2023-09-11 | 2023-09-11 | Ram air turbine power generation system with self-precooling function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117052559A (en) |
-
2023
- 2023-09-11 CN CN202311168046.XA patent/CN117052559A/en active Pending
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