CN103047012B - Ejection intercooling gas turbine - Google Patents
Ejection intercooling gas turbine Download PDFInfo
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- CN103047012B CN103047012B CN201310010156.3A CN201310010156A CN103047012B CN 103047012 B CN103047012 B CN 103047012B CN 201310010156 A CN201310010156 A CN 201310010156A CN 103047012 B CN103047012 B CN 103047012B
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- group
- turbofan
- multistage
- injector
- stage compression
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- 230000006835 compression Effects 0.000 claims abstract description 32
- 238000007906 compression Methods 0.000 claims abstract description 32
- 238000002485 combustion reaction Methods 0.000 claims abstract description 14
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims 1
- 230000002146 bilateral effect Effects 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 9
- 230000010512 thermal transition Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002372 labelling Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an ejection intercooling gas turbine. The ejection intercooling gas turbine comprises a gas compressor shell, multistage compressors, an RSS steady-flow combustor, a turbofan shell and multistage turbofans. The ejection intercooling gas turbine is divided into four portions, i.e. a first portion, a second portion, a third portion and a fourth portion which are in end-to-end connection communication, and are of bilateral symmetry through taking the same straight line as the axis; the first portion consists of a first section of the gas compressor shell, a first group of multistage compressor (3) and an ejector (1); the second portion consists of a second section of the gas compressor shell and a second group of multistage compressor (4); the third portion consists of the RSS steady-flow combustor (5); and the fourth portion consists of the turbofan shell and a group of multistage turbofan (6). According to the ejection-intercooling gas turbine, under the flowing ejection action of multistage compressed air, cold air enters an air inlet passage by passing through the ejectors, so as to be mixed with the compressed air and cool the compressed air, and then the highest combustion temperature is reduced, so that the compression pressure can be further increased, and the heat conversion efficiency is improved.
Description
Technical field
The invention belongs to gas turbine technology field is and in particular to cold gas turbine in a kind of injection.
Background technology
What compressor compression traditional gas turbine inlet air passes through, and intake air temperature rises, by turbofan, fuel gas temperature limited, after compressor, air pressure can not be too high, thus limiting the indoor thermal transition efficiency of burning.
Content of the invention
The purpose of the present invention limits burning Indoor Thermal transformation efficiency precisely in order to solving the problems, such as that intake air temperature is high, and proposes cold gas turbine in a kind of injection.
Technical scheme：
Cold gas turbine in a kind of injection, including compressor casing, multi-stage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan, is divided into four parts communicating that join end to end, each several part is all with same straight line as axle, symmetrical；
Part I, is made up of first paragraph compressor casing, first group of multi-stage compression, the first injector, second injector；First group of multi-stage compression is located in first paragraph compressor casing, and the injector of more than 2 is distributed in outside first paragraph compressor casing；This multi-stage compression front end and contact air to be compressed, first injector, the second injector front end are connected with cold air, the rear end of this multi-stage compression is connected with the rear end of the first injector, the second injector, forms air intake duct, and air intake duct is connected with Part II；
Part II, is made up of second segment compressor casing, second group of multi-stage compression；Second group of multi-stage compression is located in second segment compressor casing；This multi-stage compression front end is connected with Part I rear end, and rear end is connected with RSS steady-flow combustion device front end；
Part III, is made up of RSS steady-flow combustion device；Front end is connected with second segment compressor casing rear end, and rear end is connected with turbofan casing front end；
Part IV, is made up of turbofan casing, one group of multistage turbofan；Multistage turbofan is located in turbofan casing；Front end is connected with RSS steady-flow combustion device rear end, rear end and contact air.
Beneficial effects of the present invention：
Under the flowing ejector action of multi-stage compression air, cold air enters air intake duct through injector, mixes with compressed air, and cools down compressed air, reduces burning maximum temperature, such that it is able to improve compression pressure further, improves thermal transition efficiency.
Brief description
Fig. 1 is the structural representation of the present invention, also can be used as highly preferred embodiment of the present invention.
The each labelling of accompanying drawing represents respectively：
1- injector
2- injector
3- multi-stage compression
4- multi-stage compression
5-RSS steady-flow combustion device
The multistage turbofan of 6-
Specific embodiment
Cold gas turbine in a kind of injection, including compressor casing, multi-stage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan, is divided into four parts communicating that join end to end, each several part is all with same straight line as axle, symmetrical；
Part I, is made up of first paragraph compressor casing, first group of multi-stage compression, the first injector, second injector；First group of multi-stage compression is located in first paragraph compressor casing, and the injector of more than 2 is distributed in outside first paragraph compressor casing；This multi-stage compression front end and contact air to be compressed, first injector, the second injector front end are connected with cold air, the rear end of this multi-stage compression is connected with the rear end of the first injector, the second injector, forms air intake duct, and air intake duct is connected with Part II；
Part II, is made up of second segment compressor casing, second group of multi-stage compression；Second group of multi-stage compression is located in second segment compressor casing；This multi-stage compression front end is connected with Part I rear end, and rear end is connected with RSS steady-flow combustion device front end；
Part III, is made up of RSS steady-flow combustion device；Front end is connected with second segment compressor casing rear end, and rear end is connected with turbofan casing front end；
Part IV, is made up of turbofan casing, one group of multistage turbofan；Multistage turbofan is located in turbofan casing；Front end is connected with RSS steady-flow combustion device rear end, rear end and contact air.
Below in conjunction with the accompanying drawings, the work process of the present invention is further described.Cold gas turbine in a kind of injection of the present invention, arranges one week injector around conventional gas turbine compressor casing, and under the flowing ejector action of multi-stage compression air, air is entered air intake duct through injector and mixed with compressed air.Cold air cools down compressed air after entering, and reduces burning maximum temperature, such that it is able to improve compression pressure further, improves thermal transition efficiency.
Above content be with reference to specific preferred implementation made for the present invention further describe it is impossible to assert the present invention be embodied as be confined to these explanations.For general technical staff of the technical field of the invention, without departing from the inventive concept of the premise, some simple deduction or replace can also be made, all should be considered as belonging to protection scope of the present invention.
Claims (1)
1. cold gas turbine in a kind of injection, including compressor casing, multi-stage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan it is characterised in that being divided into four parts communicating that join end to end, each several part is all with same straight line as axle, symmetrical；Part I, is made up of first paragraph compressor casing, first group of multi-stage compression (3), the first injector (1), second injector (2)；First group of multi-stage compression (3) is located in first paragraph compressor casing, and the injector of more than 2 is distributed in outside first paragraph compressor casing；This first group of multi-stage compression (3) front end and contact air to be compressed, first injector (1), the second injector (2) front end are connected with cold air, the rear end of this first group of multi-stage compression (3) is connected with the rear end of the first injector (1), the second injector (2), composition air intake duct, air intake duct is connected with Part II；
Part II, is made up of second segment compressor casing, second group of multi-stage compression (4)；Second group of multi-stage compression (4) is located in second segment compressor casing；This second group of multi-stage compression (4) front end is connected with Part I rear end, and rear end is connected with RSS steady-flow combustion device (5) front end；
Part III, is made up of RSS steady-flow combustion device (5)；Front end is connected with second segment compressor casing rear end, and rear end is connected with turbofan casing front end；Part IV, is made up of turbofan casing, one group of multistage turbofan (6)；Multistage turbofan (6) is located in turbofan casing；Front end is connected with RSS steady-flow combustion device (5) rear end, rear end and contact air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310010156.3A CN103047012B (en) | 2013-01-11 | 2013-01-11 | Ejection intercooling gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310010156.3A CN103047012B (en) | 2013-01-11 | 2013-01-11 | Ejection intercooling gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103047012A CN103047012A (en) | 2013-04-17 |
| CN103047012B true CN103047012B (en) | 2017-02-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310010156.3A Active CN103047012B (en) | 2013-01-11 | 2013-01-11 | Ejection intercooling gas turbine |
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| Country | Link |
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| CN (1) | CN103047012B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869038A (en) * | 2018-07-02 | 2018-11-23 | 重庆交通大学 | Micro gas turbine electricity generation system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1204005A (en) * | 1997-06-26 | 1999-01-06 | 亚瑞亚·勃朗勃威力有限公司 | Jet engine |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| CN201610799U (en) * | 2009-12-18 | 2010-10-20 | 北京航空航天大学 | Variable front duct injector |
| CN201620968U (en) * | 2010-03-15 | 2010-11-03 | 张俊军 | Multielement inlet turbine rear augmentation fan engine |
| CN202659349U (en) * | 2012-06-11 | 2013-01-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Translational adjustable exhaust injector |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8127529B2 (en) * | 2007-03-29 | 2012-03-06 | United Technologies Corporation | Variable area fan nozzle and thrust reverser |
-
2013
- 2013-01-11 CN CN201310010156.3A patent/CN103047012B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1204005A (en) * | 1997-06-26 | 1999-01-06 | 亚瑞亚·勃朗勃威力有限公司 | Jet engine |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| CN201610799U (en) * | 2009-12-18 | 2010-10-20 | 北京航空航天大学 | Variable front duct injector |
| CN201620968U (en) * | 2010-03-15 | 2010-11-03 | 张俊军 | Multielement inlet turbine rear augmentation fan engine |
| CN202659349U (en) * | 2012-06-11 | 2013-01-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Translational adjustable exhaust injector |
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| Publication number | Publication date |
|---|---|
| CN103047012A (en) | 2013-04-17 |
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