CN109630219B - Gas turbine exhaust apparatus - Google Patents
Gas turbine exhaust apparatus Download PDFInfo
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- CN109630219B CN109630219B CN201811538300.XA CN201811538300A CN109630219B CN 109630219 B CN109630219 B CN 109630219B CN 201811538300 A CN201811538300 A CN 201811538300A CN 109630219 B CN109630219 B CN 109630219B
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- air inlet
- channels
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- gas turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application discloses gas turbine exhaust apparatus, it includes: a transition section of circular or ring structure having 2nA fan-shaped or fan-ring-shaped air inlet channel; the diffusion section is connected to the transition section and is provided with turning channels with the same number of air inlet channels, the air inlet ends and the air outlet ends of the turning channels are perpendicular to each other, and the turning channels are provided with air inlet ports and rectangular air outlet ports which are the same as the air inlet channels in shape; and the convergence section is fixed at the air outlet end of the diffusion section and is used for converging the steering channel into a whole. The application discloses gas turbine exhaust apparatus carries out split type design through the flow path with exhaust apparatus, realizes through the changeover portion that the import gas reposition of redundant personnel is 2nIt is individual, later through diffusion section speed reduction and deflection, reduced gas equivalent turning radius ratio, assemble into a flow path through the section of converging at last, and have concurrently and draw penetrating, the rectification function, this application makes the gas flow more stable, flow direction more regular, total pressure loss is littleer.
Description
Technical Field
The application belongs to the technical field of gas turbine design, and particularly relates to a gas turbine exhaust device.
Background
Gas turbine exhaust systems are classified into a front shaft output type and a rear shaft output type in terms of the form of the output shaft. The front shaft output type exhaust device is relatively simple in structure, and fuel gas is discharged in a deflected mode in a regular flow path; the rear axle output type has a complicated flow path profile and structure inside the rear axle output type because the output shaft passes through the exhaust device. The rear output type exhaust device is partially designed into a structure with a circular inlet and a rectangular outlet under the limitation of the structure of the rear turbine casing. The existing circular-square exhaust device adopts a flow path integrated structure, the problems of obvious gas flow separation, disordered flow direction, unstable airflow, large total pressure loss and the like exist in the flow path form, and the exhaust device is difficult to assemble and disassemble, low in fault positioning accuracy and difficult to maintain in daily life.
Disclosure of Invention
It is an object of the present application to provide a gas turbine exhaust to solve any of the above problems.
The technical scheme of the application is as follows: a gas turbine exhaust, comprising: a transition section of circular or annular configuration, the transition section having 2nA fan-shaped or fan-ring-shaped air inlet channel; the diffusion section is connected to the transition section and is provided with steering channels with the same number of air inlet channels, the air inlet ends and the air outlet ends of the steering channels are perpendicular to each other, and the steering channels are provided with air inlet ports and rectangular air outlet ports which are the same as the air inlet channels in shape; and the convergence section is fixed at the air outlet end of the diffusion section and is used for converging the steering channel into a whole.
In the present application, the flow path area of the intake passage of the transition section is constant.
In this application, the turning channel of the diffuser section gradually increases in flow path area from the inlet port to the outlet port.
In the present application, the convergent section is a convergent structure, and the flow path area thereof is gradually reduced.
In the present application, the intake passage and the diverting passage are both symmetrical with a bisecting plane, wherein the bisecting plane passes through the axis of the circular or toroidal shape.
The application discloses gas turbine exhaust apparatus carries out split type design through the flow path with exhaust apparatus, realizes through the changeover portion that the import gas reposition of redundant personnel is 2nAnd finally, the equivalent turning radius ratio is greatly reduced by decelerating and deflecting through the diffusion section, and the equivalent turning radius ratio is converged into a flow path through the convergence section, and the equivalent turning radius ratio has the functions of injection and rectification. The gas of the exhaust device is stable in flowing, the flowing direction is more regular, the total pressure loss is less, the dismounting is simple, the fault positioning accuracy is high, and the maintenance is convenient.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a structural view of a gas turbine exhaust system according to the present application.
FIG. 2 is a side view of a gas turbine exhaust of the present application.
Fig. 3 is a diagram of a transition section structure of the present application.
Fig. 4 is a view showing the structure of a diffuser section of the present application.
Fig. 5 is a diagram of a convergence section structure of the present application.
FIG. 6 is a schematic representation of several flow paths formed by the gas turbine exhaust of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The application aims at providing a gas turbine exhaust apparatus, can make the gas flow in the exhaust apparatus more stable, flow direction more regular, total pressure loss is littleer, and has the function that the dismouting is simple, the fault location degree of accuracy is high, it is convenient to maintain.
To this end, the gas turbine exhaust of the present application assumes a split flow path design, which includes a transition section 10, a diffuser section 20, and a converging section 30. The transition section 10 is of circular or annular configuration, and the transition section 10 has 2nA fan-shaped or fan-shaped air inlet channel, the diffusion section 2 is connected to the transition section 10, the diffusion section 20 is provided with turning channels with the same number of air inlet channels, the air inlet end and the air outlet end of the turning channels are vertical to each other, the turning channels are provided with air inlet ports and rectangular air outlet ports with the same shape as the air inlet channels, the convergence section 30 is fixed at the air outlet end of the diffusion section 20 and is used for converging 2nThe strip turning channels are an integrated main flow path. Wherein n is more than or equal to 1, and n is a natural number.
The gas turbine exhaust device adopts a split flow path design, and firstly divides the gas into 2nThe strip flow path is converged into a total flow path after being turned, so that the gas flow is more stable, the flow direction is more regular, and the total pressure loss is less.
Referring to fig. 1 to 6, an embodiment of n-3 in the present application is shown, and this embodiment is described in the present applicationIn the example, the gas turbine exhaust apparatus is composed of a transition section 10, a diffuser section 20 and a convergent section 30, the section of the transition section 10 is circular, the section of the convergent section 30 is rectangular, and the transition section 10 has 2nThe flow path area (cross section) of the air inlet passages 11-18 is uniform and constant, namely 8 fan-shaped annular air inlet passages 11-18 are equally divided. The diffuser section 20 is an expanding structure having the same number of turning channels as the number of the intake channels, the intake ends 21 of the turning channels are the same as the shape of the intake channels and include the intake ports 211 and 218, and the flow path area of each turning channel is gradually increased, so that the diffuser section 20 is also gradually increased as a whole. The convergent section 30 is a convergent structure, the flow path area is gradually reduced, the convergent section is roughly in a trapezoidal structure, the bottom surface 32 of the trapezoidal structure is connected with a plurality of diversion channels, and the airflow converged into an integral type in the convergent section 30 flows out from the top surface 31 of the trapezoidal structure.
The transition section 10 is welded with the diffusion section 20, and the gas is realized 2 in the transition section 10nThe speed, pressure and deflection direction of the flow are unchanged. The other end of the diffusion section 20 is fixedly connected with the convergence section 30, the fuel gas diffuses and deflects in the diffusion section 20, the speed is greatly reduced, the pressure is increased, and the deflection of 90 degrees is realized in the flowing direction. The area of the inlet of the convergence section 30 is larger than the area of the outlet of the diffusion section 20, so that the injection function is realized, and meanwhile, the turbulent gas rectification is realized, so that the temperature of the gas outlet is lower, and the velocity field is more uniform.
In the present application, the intake passage and the turning passage are both symmetrical about a bisecting plane, wherein the bisecting plane passes through the axis of the circular or toroidal shape. Specifically, referring to fig. 4, the bisecting plane (not shown) is a plane passing through the turning channel axis, and this plane makes the inlet port 211 and the inlet port 212 bilaterally symmetrical, the inlet port 213 and the inlet port 214 bilaterally symmetrical, the inlet port 215 and the inlet port 216 bilaterally symmetrical, and the inlet port 217 and the inlet port 218 bilaterally symmetrical, and makes the outlet port 221 and the outlet port 222 bilaterally symmetrical, the outlet port 223 and the outlet port 224 bilaterally symmetrical, the outlet port 225 and the outlet port 226 bilaterally symmetrical, and the outlet port 227 and the outlet port 228 bilaterally symmetrical. Finally, a first diversion channel is formed between the air inlet port 211 and the air outlet port 221, a second diversion channel is formed between the air inlet port 212 and the air outlet port 222,A third diversion channel is formed between the air inlet port 213 and the air outlet port 223, a fourth diversion channel is formed between the air inlet port 214 and the air outlet port 224, a fifth diversion channel is formed between the air inlet port 215 and the air outlet port 225, a sixth diversion channel is formed between the air inlet port 216 and the air outlet port 2226, a seventh diversion channel is formed between the air inlet port 217 and the air outlet port 227, and an eighth diversion channel is formed between the air inlet port 218 and the air outlet port 228, wherein the eight diversion channels are 2 in total38.
The utility model provides a gas turbine exhaust apparatus carries out split type design through with exhaust apparatus diffusion section, and the changeover portion realizes that import gas shunts, and diffusion section realizes 2nThe deflection of a flow path, greatly reduced gas equivalent turning radius ratio (turning radius and flow path equivalent diameter ratio), make the gas flow more stable, flow direction rule more, total pressure loss greatly reduced, the convergence section assembles the gas of reposition of redundant personnel for whole, and it has to draw and penetrate and the rectification function concurrently, and the gas turbine exhaust apparatus dismouting of this application is simple, fault location degree of accuracy is high, the maintenance is convenient.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. A gas turbine exhaust, comprising:
a transition section (10), the transition section (10) being of a circular or toroidal configuration, and the transition section (10) having 2nA fan-shaped or fan-ring-shaped air inlet channel;
the diffuser section (20) is connected to the transition section (10), the diffuser section (20) is provided with turning channels with the same number of air inlet channels, the air inlet ends and the air outlet ends of the turning channels are perpendicular to each other, and the turning channels are provided with air inlet ports and rectangular air outlet ports which are the same as the air inlet channels in shape; and
the convergent section (30) is rectangular and fixed at the air outlet end of the diffusion section (20) and is used for converging the turning channel into a whole, wherein the convergent section (30) is of a contraction structure, and the flow path area of the convergent section is gradually reduced.
2. A gas turbine exhaust arrangement according to claim 1, characterised in that the flow area of the inlet passage of the transition section (10) is constant.
3. The gas turbine exhaust of claim 1, wherein the turning passages of the diffuser section (20) increase in flow area from an inlet port to an outlet port.
4. A gas turbine exhaust according to any one of claims 1 to 3, wherein the inlet passage and the diversion passage are each symmetrical about a bisecting plane, wherein the bisecting plane passes through the axis of the circular or toroidal shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538300.XA CN109630219B (en) | 2018-12-16 | 2018-12-16 | Gas turbine exhaust apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538300.XA CN109630219B (en) | 2018-12-16 | 2018-12-16 | Gas turbine exhaust apparatus |
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| Publication Number | Publication Date |
|---|---|
| CN109630219A CN109630219A (en) | 2019-04-16 |
| CN109630219B true CN109630219B (en) | 2022-03-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811538300.XA Active CN109630219B (en) | 2018-12-16 | 2018-12-16 | Gas turbine exhaust apparatus |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114776404B (en) * | 2022-04-14 | 2023-11-28 | 中国航发沈阳发动机研究所 | Rectifying support plate structure of exhaust device |
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| US8221073B2 (en) * | 2008-12-22 | 2012-07-17 | Pratt & Whitney Canada Corp. | Exhaust gas discharge system and plenum |
| US8870532B2 (en) * | 2010-11-15 | 2014-10-28 | General Electric Company | Exhaust hood diffuser |
| PL221113B1 (en) * | 2012-01-25 | 2016-02-29 | Gen Electric | Turbine exhaust diffuser system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB685114A (en) * | 1949-03-19 | 1952-12-31 | Power Jets Res & Dev Ltd | Improvements in or relating to combustion apparatus |
| US3927521A (en) * | 1974-01-16 | 1975-12-23 | Westinghouse Electric Corp | Multicone exhaust diffuser system for a gas turbine |
| US3981143A (en) * | 1974-08-15 | 1976-09-21 | The United States Of America As Represented By The Secretary Of The Army | Infrared suppressor |
| CN85108352A (en) * | 1984-11-12 | 1986-05-10 | 阿芒·罗侬 | The vent systems that is used for the internal-combustion engine combustion gas |
| CN101509427A (en) * | 2008-02-11 | 2009-08-19 | 通用电气公司 | Exhaust stacks and power generation systems for increasing gas turbine power output |
| EP2357323A2 (en) * | 2010-02-17 | 2011-08-17 | General Electric Company | Exhaust diffuser |
| CN102374030A (en) * | 2010-08-06 | 2012-03-14 | 通用电气公司 | Contoured axial-radial exhaust diffuser |
| CN101975652A (en) * | 2010-11-18 | 2011-02-16 | 中国人民解放军国防科学技术大学 | Ultrasonic-velocity free vortex wind tunnel |
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| WO2018102047A1 (en) * | 2016-11-30 | 2018-06-07 | Dresser-Rand Company | Compact gas turbine exhaust system |
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| CN109630219A (en) | 2019-04-16 |
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