CN103047012A - Ejection intercooling gas turbine - Google Patents
Ejection intercooling gas turbine Download PDFInfo
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- CN103047012A CN103047012A CN2013100101563A CN201310010156A CN103047012A CN 103047012 A CN103047012 A CN 103047012A CN 2013100101563 A CN2013100101563 A CN 2013100101563A CN 201310010156 A CN201310010156 A CN 201310010156A CN 103047012 A CN103047012 A CN 103047012A
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- multistage
- turbofan
- group
- gas turbine
- ejection
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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 the gas turbine technology field, be specifically related to cold gas turbine in a kind of injection.
Background technique
Traditional gas turbine inlet air is through what gas compressor compression, and intake temperature rises, and is subject to turbofan to the restriction of fuel gas temperature, and air pressure can not be too high behind the gas compressor, thereby limited the thermal transition efficient in the firing chamber.
Summary of the invention
Purpose of the present invention limits the problem of thermal transition efficient in the firing chamber in order to solve the intake temperature height just, and proposes cold gas turbine in a kind of injection.
Technological scheme of the present invention:
Cold gas turbine in a kind of injection comprises compressor casing, multistage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan, is divided into four parts that join end to end and communicate, and each several part is all take same straight line as axle, bilateral symmetry;
First portion is comprised of first paragraph compressor casing, first group of multistage compression, ejector; First group of multistage compression is positioned at the first paragraph compressor casing, and the ejector more than 2 is distributed in outside the first paragraph compressor casing; This multistage compression front end is connected with air to be compressed, and the ejector front end is connected with cool air, and the rear end of this multistage compression is connected with the rear end of ejector, forms intake duct, and intake duct is connected with second portion;
Second portion is comprised of second segment compressor casing, second group of multistage compression; Second group of multistage compression is positioned at the second segment compressor casing; This multistage compression front end is connected with the first portion rear end, and the rear end is connected with RSS steady-flow combustion device front end;
Third part is comprised of RSS steady-flow combustion device; Front end is connected with second segment compressor casing rear end, and the rear end is connected with turbofan casing front end;
The 4th part is comprised of turbofan casing, one group of multistage turbofan; Multistage turbofan is positioned at the turbofan casing; Front end is connected with RSS steady-flow combustion device rear end, and the rear end is connected with air.
Beneficial effect of the present invention:
Under the mobile ejector action of multistage compression air, cool air enters intake duct through ejector, mix with pressurized air, and cooled compressed air, reduce the burning maximum temperature, thereby can further improve compression pressure, improve thermal transition efficient.
Description of drawings
Fig. 1 is structural representation of the present invention, also can be used as most preferred embodiment of the present invention.
Each mark of accompanying drawing represents respectively:
The 1-ejector
The 2-ejector
The 3-multistage compression
The 4-multistage compression
5-RSS steady-flow combustion device
The multistage turbofan of 6-
Embodiment
Cold gas turbine in a kind of injection comprises compressor casing, multistage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan, is divided into four parts that join end to end and communicate, and each several part is all take same straight line as axle, bilateral symmetry;
First portion is comprised of first paragraph compressor casing, first group of multistage compression, ejector; First group of multistage compression is positioned at the first paragraph compressor casing, and the ejector more than 2 is distributed in outside the first paragraph compressor casing; This multistage compression front end is connected with air to be compressed, and the ejector front end is connected with cool air, and the rear end of this multistage compression is connected with the rear end of ejector, forms intake duct, and intake duct is connected with second portion;
Second portion is comprised of second segment compressor casing, second group of multistage compression; Second group of multistage compression is positioned at the second segment compressor casing; This multistage compression front end is connected with the first portion rear end, and the rear end is connected with RSS steady-flow combustion device front end;
Third part is comprised of RSS steady-flow combustion device; Front end is connected with second segment compressor casing rear end, and the rear end is connected with turbofan casing front end;
The 4th part is comprised of turbofan casing, one group of multistage turbofan; Multistage turbofan is positioned at the turbofan casing; Front end is connected with RSS steady-flow combustion device rear end, and the rear end is connected with air.
Below in conjunction with accompanying drawing, working procedure of the present invention is further described.Cold gas turbine in a kind of injection of the present invention, at conventional gas turbine compressor casing arranged around one all ejectors, under the mobile ejector action of multistage compression air, air enters intake duct through ejector to be mixed with pressurized air.Cool air enters rear cooled compressed air, has reduced the burning maximum temperature, thereby can further improve compression pressure, improves thermal transition efficient.
Above content is the further description of the present invention being done in conjunction with concrete preferred implementation, can not assert that implementation of the present invention is confined to these explanations.For the general technical staff of the technical field of the invention, without departing from the inventive concept of the premise, can also make some simple deduction or replace, all should be considered as belonging to protection scope of the present invention.
Claims (1)
1. cold gas turbine in the injection comprises compressor casing, multistage compression, RSS steady-flow combustion device, turbofan casing, multistage turbofan, it is characterized in that, is divided into four parts that join end to end and communicate, and each several part is all take same straight line as axle, bilateral symmetry; First portion is comprised of first paragraph compressor casing, first group of multistage compression (3), ejector (1); First group of multistage compression (3) is positioned at the first paragraph compressor casing, and the ejector more than 2 (1) is distributed in outside the first paragraph compressor casing; This multistage compression (3) front end is connected with air to be compressed, ejector (1) front end is connected with cool air, the rear end of this multistage compression (3) is connected with the rear end of ejector (1), forms intake duct, and intake duct is connected with second portion;
Second portion is comprised of second segment compressor casing, second group of multistage compression (4); Second group of multistage compression (4) is positioned at the second segment compressor casing; This multistage compression (4) front end is connected with the first portion rear end, and the rear end is connected with RSS steady-flow combustion device (5) front end;
Third part is comprised of RSS steady-flow combustion device (5); Front end is connected with second segment compressor casing rear end, and the rear end is connected with turbofan casing front end; The 4th part is comprised of turbofan casing, one group of multistage turbofan (6); Multistage turbofan (6) is positioned at the turbofan casing; Front end is connected with RSS steady-flow combustion device (5) rear end, and the rear end is connected with 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 true CN103047012A (en) | 2013-04-17 |
| CN103047012B CN103047012B (en) | 2017-02-08 |
Family
ID=48059821
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 |
Country Status (1)
| Country | Link |
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| CN (1) | CN103047012B (en) |
Cited By (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 (6)
| 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 |
| US20100257841A1 (en) * | 2007-03-29 | 2010-10-14 | Pero Edward B | Variable area fan nozzle and thrust reverser |
| 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 |
-
2013
- 2013-01-11 CN CN201310010156.3A patent/CN103047012B/en active Active
Patent Citations (7)
| 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 |
| US20100257841A1 (en) * | 2007-03-29 | 2010-10-14 | Pero Edward B | Variable area fan nozzle and thrust reverser |
| 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 |
| US20100170984A1 (en) * | 2007-06-01 | 2010-07-08 | Airbus Operations | Engine assembly for aircraft with sliding nancelle |
| 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 |
Cited By (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 |
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| Publication number | Publication date |
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| CN103047012B (en) | 2017-02-08 |
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