CN112065585A - Gas turbine exhaust structure - Google Patents
Gas turbine exhaust structure Download PDFInfo
- Publication number
- CN112065585A CN112065585A CN202010987799.3A CN202010987799A CN112065585A CN 112065585 A CN112065585 A CN 112065585A CN 202010987799 A CN202010987799 A CN 202010987799A CN 112065585 A CN112065585 A CN 112065585A
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- CN
- China
- Prior art keywords
- gas turbine
- exhaust
- duct
- casing
- exhaust pipe
- 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.)
- Pending
Links
- 239000011810 insulating material Substances 0.000 claims description 5
- 239000007789 gas Substances 0.000 abstract description 46
- 230000005855 radiation Effects 0.000 abstract description 7
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 abstract description 6
- 239000003546 flue gas Substances 0.000 abstract description 6
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 239000012774 insulation material Substances 0.000 abstract 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 4
- 230000001629 suppression Effects 0.000 description 4
- 239000000779 smoke Substances 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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)
Abstract
The invention discloses an exhaust structure of a gas turbine, and belongs to the technical field of gas turbine flue gas emission. The structure comprises a gas turbine shell, wherein an air supply assembly is arranged at an air inlet of the gas turbine shell, an exhaust volute is arranged at an air outlet of the gas turbine shell, the gas turbine shell comprises an outer casing and an inner casing, the inner casing is inserted into the inner side of the outer casing, an inner duct is formed on the inner side of the inner casing, an outer duct is formed between the inner casing and the outer casing, and the exhaust volute is communicated with the outer duct and the inner duct. The gas turbine adopts a double-duct gas turbine with a small duct ratio, and the outer duct is internally provided with cold air, so that the surface temperature of a shell of the gas turbine is favorably reduced, the infrared radiation is favorably reduced, the stealth performance of the gas turbine is improved, and the service life of hot end parts of the gas turbine is favorably prolonged. The surface temperature and the exhaust temperature of the exhaust volute are reduced by utilizing the cold air in the outer duct, and the outer wall of the outer exhaust pipe is wrapped with heat insulation materials, so that the stealth performance of the exhaust volute is improved.
Description
Technical Field
The invention relates to an exhaust structure of a gas turbine, and belongs to the technical field of gas turbine smoke emission.
Background
The gas turbine is required to have stealth performance in some special fields, such as stealth warships, reefs, military mobile power stations and the like, except for adopting stealth materials and a stealth process, the gas turbine is a heat source, particularly an exhaust port of the gas turbine, is most easily detected by an infrared radar, and the gas turbine, whether moving or fixed, is easily targeted. Moreover, with the technical development of the gas turbine, the high pressure ratio (30-40) and the high initial temperature of the fuel gas (as high as 1800K) further increase the exhaust temperature, the wall temperature of the exhaust pipeline is increased accordingly, and the higher the wall temperature is, the greater the heat radiation is, the easier the heat radiation is to be detected by the infrared radar.
Chinese patent publication No. CN110500147A discloses an infrared suppression device for flue gas emission from ships, wherein flue gas passes through an installation part, enters a flue gas main flow pipe and a flue gas branch flow area of the infrared suppression part, and is buffered and decompressed layer by layer to slow down the emission speed, at this time, a water circulation device of a condenser is opened to make cold water enter a cold guide pipe and a cold accumulation layer from a water inlet, then cold water sequentially enters the snake-shaped communicated cold guide pipe, and then the cold water of the cold guide pipe and the cold accumulation layer is mixed and discharged at a water outlet, thereby realizing the cooling of the flue gas emission from ships.
However, this device has the following disadvantages: firstly, the infrared suppression equipment is arranged on a ship smoke discharge pipeline, the temperature of the exhaust pipeline is high under the influence of smoke, and the infrared suppression equipment is still easily detected by an infrared radar; and secondly, the infrared inhibition equipment needs to be matched with a condenser circulating system for use, so that the equipment investment is large and the energy consumption is high.
Disclosure of Invention
In order to solve the technical problem, the invention provides an exhaust structure of a gas turbine.
The invention is realized by the following technical scheme:
the invention provides a gas turbine exhaust structure which comprises a gas turbine shell, wherein an air supply assembly is arranged at an air inlet of the gas turbine shell, an exhaust volute is arranged at an exhaust outlet, the gas turbine shell comprises an outer casing and an inner casing, the inner casing is inserted into the inner side of the outer casing, an inner duct is formed on the inner side of the inner casing, an outer duct is formed between the inner casing and the outer casing, and the exhaust volute is communicated with the outer duct and the inner duct.
And the outer side of the exhaust volute is wrapped with a heat insulating material.
The exhaust volute comprises an outer exhaust pipe and an inner exhaust pipe, the inner exhaust pipe is located on the inner side of the outer exhaust pipe, and the inner exhaust pipe is connected with the outer exhaust pipe through a plurality of ribs.
The inner exhaust pipe is communicated with the inner duct, and a flow passage between the outer exhaust pipe and the inner exhaust pipe is communicated with the outer duct.
And the air outlet of the outer exhaust pipe is flush with the air outlet of the inner exhaust pipe.
The outer casing and the inner casing both extend to the air outlet of the air supply assembly.
The air supply assembly comprises a fan casing and a fan arranged on the inner side of the fan casing.
The invention has the beneficial effects that:
1. the gas turbine adopts a double-duct gas turbine with a small duct ratio, and the outer duct is internally provided with cold air, so that the surface temperature of a shell of the gas turbine is favorably reduced, the infrared radiation is favorably reduced, the stealth performance of the gas turbine is improved, and the service life of hot end parts of the gas turbine is favorably prolonged.
2. The surface temperature and the exhaust temperature of the exhaust volute are reduced by utilizing the cold air in the outer duct, and the outer wall of the outer exhaust pipe is wrapped with a heat insulating material, so that the heat radiation of the exhaust volute is reduced, and the stealth performance of the exhaust volute is improved.
3. The gas discharged from the inner exhaust pipe is mixed with the gas discharged from the space between the inner exhaust pipe and the outer exhaust pipe and discharged at the outlet of the exhaust volute, which is beneficial to reducing the exhaust temperature.
4. On the basis of the original structure of the small-bypass-ratio double-bypass aero-engine, the invisible performance of the gas turbine can be improved by redesigning the exhaust volute, the investment is small, and the energy consumption is low.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
In the figure: 1-fixed block, 2-fan, 3-fan casing, 4-outer casing, 5-outer duct rear section, 6-outer duct, 7-inner duct, 8-outer exhaust pipe, 9-rib, 10-inner exhaust pipe and 11-inner casing.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1, the gas turbine exhaust structure according to the present invention includes a gas turbine housing, an air supply assembly is installed at an air inlet of the gas turbine housing, an exhaust volute is installed at an air outlet, the gas turbine housing includes an outer casing 4 and an inner casing 11, the inner casing 11 is inserted into an inner side of the outer casing 4, an inner duct 7 is formed at an inner side of the inner casing 11, an outer duct 6 is formed between the inner casing 11 and the outer casing 4, and the exhaust volute is communicated with the outer duct 6 and the inner duct 7. When in use, the outer casing 4 is connected with the inner casing 11 through the fixing block 1. The rear end of the outer casing 4 is connected with the exhaust volute through an outer duct rear section 5.
And the outer side of the exhaust volute is wrapped with a heat insulating material. The surface temperature of the exhaust volute is isolated, and the stealth performance of the exhaust volute is improved.
The exhaust volute comprises an outer exhaust pipe 8 and an inner exhaust pipe 10, the inner exhaust pipe 10 is located on the inner side of the outer exhaust pipe 8, and the inner exhaust pipe 10 is connected with the outer exhaust pipe 8 through a plurality of ribs 9.
The inner exhaust pipe 10 is communicated with the inner duct 7, and a flow passage between the outer exhaust pipe 8 and the inner exhaust pipe 10 is communicated with the outer duct 6.
And the air outlet of the outer exhaust pipe 8 is flush with the air outlet of the inner exhaust pipe 10. The gas discharged from the inner exhaust pipe 10 is mixed with the gas discharged from the flow channel between the outer exhaust pipe 8 and the inner exhaust pipe 10 and discharged at the outlet, which is helpful for reducing the temperature of the outlet of the exhaust volute.
The outer casing 4 and the inner casing 11 both extend to the air outlet of the air supply assembly.
The air supply assembly comprises a fan casing 3 and a fan 2 arranged on the inner side of the fan casing 3.
When the small-bypass-ratio double-bypass aero-engine is changed into a gas turbine, the top cutting of the fan 2 or the redesign of the low-pressure compressor can be omitted, the fixed block 1, the fan 2, the fan case 3, the outer case 4, the outer-bypass rear section 5, the outer bypass 6 and the inner bypass 7 are reserved, and the double-layer exhaust volute is redesigned.
In the operation process of the gas turbine, gas is filled in the inner duct 7, and the gas is exhausted through the inner exhaust pipe 10 after acting on the gas turbine and the power turbine. The outer duct 6 is internally provided with cold air, which is beneficial to reducing the surface temperature of the gas turbine shell and reducing the infrared radiation; after cold air in the outer duct 6 enters the exhaust volute, the inner exhaust pipe 10 is cooled and finally discharged from a flow passage between the inner exhaust pipe 10 and the outer exhaust pipe 8, and the reduction of the surface temperature and the exhaust temperature of the exhaust volute is facilitated. The outer wall of the outer exhaust pipe 8 is wrapped with a heat insulating material, which is beneficial to reducing the heat radiation of the exhaust volute. The gas discharged from the inner exhaust pipe 10 is mixed with the gas discharged between the inner exhaust pipe 10 and the outer exhaust pipe 8 and discharged at the outlet of the exhaust volute, which helps to reduce the exhaust temperature.
Claims (7)
1. A gas turbine exhaust structure characterized in that: the gas turbine engine is characterized by comprising a gas turbine shell, wherein an air supply assembly is arranged at an air inlet of the gas turbine shell, an exhaust volute is arranged at an exhaust outlet of the gas turbine shell, the gas turbine shell comprises an outer casing (4) and an inner casing (11), the inner casing (11) is inserted into the inner side of the outer casing (4), an inner duct (7) is formed in the inner side of the inner casing (11), an outer duct (6) is formed between the inner casing (11) and the outer casing (4), and the exhaust volute is communicated with the outer duct (6) and the inner duct (7).
2. The gas turbine exhaust structure according to claim 1, wherein: and the outer side of the exhaust volute is wrapped with a heat insulating material.
3. The gas turbine exhaust structure according to claim 1, wherein: the exhaust volute comprises an outer exhaust pipe (8) and an inner exhaust pipe (10), the inner exhaust pipe (10) is located on the inner side of the outer exhaust pipe (8), and the inner exhaust pipe (10) is connected with the outer exhaust pipe (8) through a plurality of ribs (9).
4. The gas turbine exhaust structure according to claim 3, wherein: the inner exhaust pipe (10) is communicated with the inner duct (7), and a flow passage between the outer exhaust pipe (8) and the inner exhaust pipe (10) is communicated with the outer duct (6).
5. The gas turbine exhaust structure according to claim 3, wherein: the air outlet of the outer exhaust pipe (8) is flush with the air outlet of the inner exhaust pipe (10).
6. The gas turbine exhaust structure according to claim 1, wherein: the outer casing (4) and the inner casing (11) both extend to the air outlet of the air supply assembly.
7. The gas turbine exhaust structure according to claim 1, wherein: the air supply assembly comprises a fan casing (3) and a fan (2) arranged on the inner side of the fan casing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010987799.3A CN112065585A (en) | 2020-09-18 | 2020-09-18 | Gas turbine exhaust structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010987799.3A CN112065585A (en) | 2020-09-18 | 2020-09-18 | Gas turbine exhaust structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112065585A true CN112065585A (en) | 2020-12-11 |
Family
ID=73681836
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010987799.3A Pending CN112065585A (en) | 2020-09-18 | 2020-09-18 | Gas turbine exhaust structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112065585A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5746047A (en) * | 1982-07-08 | 1998-05-05 | Gereral Electric Company | Infrared suppressor |
| JPH11166451A (en) * | 1997-10-31 | 1999-06-22 | General Electric Co <Ge> | Chevron type exhaust nozzle |
| CN101365870A (en) * | 2005-08-01 | 2009-02-11 | 西科尔斯基飞机公司 | Infrared suppression system |
| CN101592081A (en) * | 2009-06-05 | 2009-12-02 | 中国航空动力机械研究所 | A kind of gas turbine generating engine |
| CN104696074A (en) * | 2013-12-10 | 2015-06-10 | 贵州黎阳航空动力有限公司 | Structure for reducing internal temperature of wall surface and machine pry of gas turbine |
| CN108843453A (en) * | 2018-08-07 | 2018-11-20 | 郑州佛光发电设备有限公司 | Exhaust silencing and cooling device and vehicle-mounted micro gas turbine generator set |
-
2020
- 2020-09-18 CN CN202010987799.3A patent/CN112065585A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5746047A (en) * | 1982-07-08 | 1998-05-05 | Gereral Electric Company | Infrared suppressor |
| JPH11166451A (en) * | 1997-10-31 | 1999-06-22 | General Electric Co <Ge> | Chevron type exhaust nozzle |
| CN101365870A (en) * | 2005-08-01 | 2009-02-11 | 西科尔斯基飞机公司 | Infrared suppression system |
| CN101592081A (en) * | 2009-06-05 | 2009-12-02 | 中国航空动力机械研究所 | A kind of gas turbine generating engine |
| CN104696074A (en) * | 2013-12-10 | 2015-06-10 | 贵州黎阳航空动力有限公司 | Structure for reducing internal temperature of wall surface and machine pry of gas turbine |
| CN108843453A (en) * | 2018-08-07 | 2018-11-20 | 郑州佛光发电设备有限公司 | Exhaust silencing and cooling device and vehicle-mounted micro gas turbine generator set |
Non-Patent Citations (3)
| Title |
|---|
| 中国大百科全书总编辑委员会: "《中国大百科全书 机械工程 2》", 30 October 1998 * |
| 张相炎: "《"十三五"江苏省高等学校重点教材 装甲车辆总体设计》", 31 July 2017 * |
| 朱英富、张国良: "《舰船隐身技术》", 30 April 2015 * |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201211 |