CN106762155B - Reverse boosting type air source system based on turbine-compressor - Google Patents
Reverse boosting type air source system based on turbine-compressor Download PDFInfo
- Publication number
- CN106762155B CN106762155B CN201611161276.3A CN201611161276A CN106762155B CN 106762155 B CN106762155 B CN 106762155B CN 201611161276 A CN201611161276 A CN 201611161276A CN 106762155 B CN106762155 B CN 106762155B
- Authority
- CN
- China
- Prior art keywords
- compressor
- turbine
- air
- pressure
- ejector
- Prior art date
- 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.)
- Active
Links
Images
Classifications
-
- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The invention relates to an aircraft air source system, in particular to a reverse boosting type air source system based on a turbine-compressor. The system comprises a turbine-compressor air circulation refrigerating system, an ejector and a precooler, wherein high-pressure gas of the engine is expanded by a turbine of the turbine-compressor air circulation refrigerating system to do work so as to achieve the cooling effect, and the cooled gas is discharged by the ejector; after compressing the outside atmosphere, a compressor of the air circulation refrigeration system of the turbine-compressor precools the compressed outside atmosphere and then enters a downstream air supply system; the ejector is located downstream of the precooler cold-side air outlet.
Description
Technical Field
The invention relates to an aircraft air source system, in particular to a reverse boosting type air source system based on a turbine-compressor.
Background
The schematic diagram of a traditional turboprop air source system is shown in fig. 1, high-temperature and high-pressure gas from a high-pressure compressor of an engine enters the air source system after being subjected to pressure regulation by a pressure regulation shutoff valve, and the gas is divided into three paths: the cold path is pre-cooled by a pre-cooler and then is fed into a downstream system; the hot bypass is provided with a precooler hot bypass valve for accurately adjusting the outlet temperature of the precooler; one way of the ejector is mainly used in a ground cooling state, the aircraft has ram air to provide heat sink for the precooler in a high altitude state, the aircraft is static without a ram head on the ground and cannot provide cooling air for the precooler, the ejector is used in the state to meet the requirements of ground cooling use, the air in the ejector way enters the ejector and is discharged after the valve of the ejector is opened, and after the speed is increased by the nozzle of the ejector, a negative pressure zone is formed at the downstream of the ejector, so that a large pressure difference is formed, the air flow at the cold edge of the precooler is promoted, and the precooling effect of the precooler is realized. In the technical scheme, the gas for the injection passage is also derived from the bleed air of the engine, and once the injector is started in a ground shutdown state, the bleed air quantity of the engine can be improved by 100% -200% on the original basis, and if the bleed air quantity of the engine is limited, the use of a downstream system of an air source system cannot be met.
Disclosure of Invention
The purpose of the invention is as follows: the air source system is suitable for the environment with insufficient air-entraining amount of the turboprop engine.
The technical scheme of the invention is as follows: a reverse pressure boosting type air source system based on a turbine-compressor is characterized in that: the system comprises a turbine-compressor air circulation refrigerating system, an ejector and a precooler, wherein high-pressure gas of the engine is expanded by a turbine of the turbine-compressor air circulation refrigerating system to do work so as to achieve the cooling effect, and the cooled gas is discharged by the ejector;
after compressing the outside atmosphere, a compressor of the air circulation refrigeration system of the turbine-compressor precools the compressed outside atmosphere and then enters a downstream air supply system;
the ejector is located downstream of the precooler cold-side air outlet.
Preferably, the turbine and the compressor of the turbo-compressor air cycle refrigeration system are mounted coaxially.
Preferably, the air supply system inlet is provided with a pressure regulating shutoff valve.
Preferably, a flow limiting device is arranged between a compressor and a precooler of the turbo-compressor air cycle refrigeration system.
The invention has the beneficial effects that: compared with the traditional scheme, the reverse boost type air source system based on the turbine-compressor changes the configuration that the main system path, the thermal bypass and the injection path bleed air from the engine due to the fact that the injector path is separated from the main air source system path, and the main system path bleed air from the engine by adopting the injection path, and the main system path compresses the external atmosphere by using the compressor, so that the air bleeding allowance of the engine is greatly improved, and the design of the air source system of the airplane under the condition that the air bleeding amount of the engine is limited can be met.
Drawings
FIG. 1 is a schematic diagram of a prior art air supply system;
fig. 2 is a schematic diagram of the principle of the present invention.
Detailed Description
The reverse boosting type air source system based on the turbine-compressor is arranged on an aircraft engine nacelle, wherein the turbine-compressor air circulation refrigeration system is a high-speed rotor accessory formed by combining a coaxial turbine and a compressor. The air source system is mainly divided into two paths in the working process: one path is high-temperature and high-pressure air led out from a high-pressure compressor of an engine, the bleed air pressure is adjusted through a pressure adjusting shutoff valve, the pressure entering a cooling turbine is kept in a constant range, the system operation is stable, the reliability of the turbine can be improved, after the high-temperature air subjected to pressure adjustment enters the turbine to perform expansion work, the air subjected to expansion cooling enters an ejector arranged on the downstream of cold side air of the precooler and is discharged under the ground state, after the speed is increased through a nozzle of the ejector, a negative pressure area is formed on the downstream of the ejector, a large pressure difference is formed, the cold side air of the precooler is enabled to flow, the precooling effect of the precooler is realized, the system can normally work under the ground state, and the ground refrigeration function of an environmental control system is met.
In the other path, in the working process, the turbine is driven by the engine bleed air to drive the coaxial compressor to rotate, the compressor sucks external atmosphere from the air inlet to compress low-temperature and low-pressure gas into high-temperature and high-pressure gas, the high-temperature and high-pressure gas passes through the flow limiting device to achieve the purpose of controlling the flow of the air source system and prevent the excessive bleed air of the air source system, the compressed high-temperature and high-pressure gas is pre-cooled by the precooler and then is fed into a downstream system, and the bypass valve of the precooler is used for accurately adjusting the temperature of. In the implementation process, technical parameters of the turbine, the compressor and the precooler need to be reasonably matched so as to ensure that the system achieves the optimal performance.
Claims (2)
1. A reverse pressure boosting type air source system based on a turbine-compressor is characterized in that: the reverse boosting type air source system comprises a turbine-compressor air circulation refrigerating system, an ejector and a precooler, high-pressure gas of the engine is expanded by a turbine of the turbine-compressor air circulation refrigerating system to do work to achieve the cooling effect, and the cooled gas is discharged by the ejector;
after compressing the outside atmosphere, a compressor of the air circulation refrigeration system of the turbine-compressor precools the compressed outside atmosphere and then enters a downstream air supply system;
the ejector is positioned at the downstream of the cold-side air outlet of the precooler, the inlet of the air source system is provided with a pressure regulating shutoff valve, and a flow limiting device is arranged between a compressor of the air circulation refrigeration system of the turbine-compressor and the precooler;
the reverse boosting type air source system is divided into two paths in the working process: one path is high-temperature and high-pressure air led out from a high-pressure compressor of an engine, the bleed air pressure is adjusted through a pressure adjusting shutoff valve, the pressure entering a cooling turbine is kept in a constant range, the system operation is ensured to be stable, the reliability of the turbine can also be improved, after the high-temperature gas subjected to pressure adjustment enters the turbine to perform expansion work, the gas subjected to expansion temperature reduction enters an ejector arranged at the downstream of cold edge air of the precooler and is discharged under the ground state, after the speed is increased through a nozzle of the ejector, a negative pressure zone is formed at the downstream of the ejector, so that a large pressure difference is formed, the cold edge air of the precooler is promoted to flow, the precooling effect of the precooler is realized, the air source system can normally work under the ground state, and the ground refrigeration function of an environmental;
in the other path, in the working process, the turbine is driven by the engine bleed air to drive the coaxial compressor to rotate, the compressor sucks external atmosphere from the air inlet to compress low-temperature and low-pressure gas into high-temperature and high-pressure gas, the high-temperature and high-pressure gas passes through the flow limiting device to achieve the purpose of controlling the flow of the air source system and prevent the excessive bleed air of the air source system, the compressed high-temperature and high-pressure gas is pre-cooled by the pre-cooler and then is fed into a downstream air supply system, and the bypass valve of the pre-cooler is used for accurately adjusting.
2. The turbocompressor-based reverse boost air supply system according to claim 1, characterized in that: the turbine and the compressor of the turbine-compressor air circulation refrigeration system are coaxially installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161276.3A CN106762155B (en) | 2016-12-15 | 2016-12-15 | Reverse boosting type air source system based on turbine-compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161276.3A CN106762155B (en) | 2016-12-15 | 2016-12-15 | Reverse boosting type air source system based on turbine-compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106762155A CN106762155A (en) | 2017-05-31 |
| CN106762155B true CN106762155B (en) | 2021-06-01 |
Family
ID=58891361
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611161276.3A Active CN106762155B (en) | 2016-12-15 | 2016-12-15 | Reverse boosting type air source system based on turbine-compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106762155B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111332477B (en) * | 2020-02-21 | 2022-09-20 | 中国电子科技集团公司第二十九研究所 | Reverse boosting turbine bypass control device and method |
| CN113236611B (en) * | 2021-06-01 | 2022-06-07 | 中国商用飞机有限责任公司 | Engine bleed air system and bleed air control method for aircraft |
| CN114483612B (en) * | 2022-03-04 | 2024-01-05 | 中国商用飞机有限责任公司 | Aerodynamic turbine compression system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5452573A (en) * | 1994-01-31 | 1995-09-26 | United Technologies Corporation | High pressure air source for aircraft and engine requirements |
| US6415595B1 (en) * | 2000-08-22 | 2002-07-09 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| US8789376B2 (en) * | 2011-05-27 | 2014-07-29 | General Electric Company | Flade duct turbine cooling and power and thermal management |
| EP3444189B1 (en) * | 2014-09-19 | 2020-06-17 | Airbus Operations GmbH | Aircraft air conditioning system and method of operating an aircraft air conditioning system |
-
2016
- 2016-12-15 CN CN201611161276.3A patent/CN106762155B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106762155A (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9765700B2 (en) | Bleed air systems for use with aircrafts and related methods | |
| US8955794B2 (en) | Bleed air systems for use with aircrafts and related methods | |
| CA2855867C (en) | Bleed air systems for use with aircrafts and related methods | |
| US10144517B2 (en) | Mixing bleed and ram air using a two turbine architecture with an outflow heat exchanger | |
| US10054051B2 (en) | Bleed air systems for use with aircraft and related methods | |
| US11466904B2 (en) | Environmental control system utilizing cabin air to drive a power turbine of an air cycle machine and utilizing multiple mix points for recirculation air in accordance with pressure mode | |
| US10247100B2 (en) | Jet engine cold air cooling system | |
| US10604263B2 (en) | Mixing bleed and ram air using a dual use turbine system | |
| US20120186267A1 (en) | Turbine integrated bleed system and method for a gas turbine engine | |
| US20130040545A1 (en) | Low pressure compressor bleed exit for an aircraft pressurization system | |
| CN106762155B (en) | Reverse boosting type air source system based on turbine-compressor | |
| US10850853B2 (en) | Environmental control system utilizing bleed pressure assist | |
| JP2012180086A (en) | Environmental control system supply precooler bypass | |
| CN105221295A (en) | A kind of punching press-turbojet compound aeroengine | |
| US10940951B2 (en) | Environmental control system utilizing multiple mix points for recirculation air in accordance with pressure mode and motor assist | |
| US20160355267A1 (en) | Recirculation system for parallel ram heat exchangers | |
| US11459110B2 (en) | Environmental control system utilizing two pass secondary heat exchanger and cabin pressure assist | |
| RU2016111698A (en) | ENGINE | |
| CN112918682B (en) | Four-wheel high-pressure water removal environment control system based on different cabin pressures and working method | |
| US20160362188A1 (en) | Fuel tank inerting apparatus for aircraft | |
| US20170305557A1 (en) | Environmental control system utilizing multiple mix points for recirculation air in accordance with pressure mode | |
| CN105620758A (en) | Air refrigeration circulating device with small ram air flow | |
| RU2545261C2 (en) | Gas turbine plant of raised efficiency | |
| CN112960126B (en) | Low-temperature fuel tank inerting system and working method thereof | |
| CN116477062A (en) | Self-adaptive adjustment electric drive inerting system and adjustment method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |