CN114151195A - Novel exhaust diffuser structure capable of improving pneumatic performance - Google Patents
Novel exhaust diffuser structure capable of improving pneumatic performance Download PDFInfo
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- CN114151195A CN114151195A CN202111468432.1A CN202111468432A CN114151195A CN 114151195 A CN114151195 A CN 114151195A CN 202111468432 A CN202111468432 A CN 202111468432A CN 114151195 A CN114151195 A CN 114151195A
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- support plate
- exhaust diffuser
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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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- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a novel exhaust diffuser structure capable of improving aerodynamic performance, which comprises a two-dimensional in-line bent support plate or a three-dimensional bent support plate. The flow separation of the air flow with the rotational flow discharged by the upstream power turbine is reduced when the air flow flows through the support plate, the total pressure loss is reduced, and the static pressure recovery performance of the exhaust diffuser is further improved. The curvature of the molded line of the two-dimensional in-line bent support plate or the three-dimensional bent support plate in the novel exhaust diffuser structure on the wall surface of the hub and the thickness of the whole support plate can be matched and designed according to the rotational flow strength and the flow of the exhaust gas of the upstream power turbine, so that the optimal performance of the exhaust diffuser is achieved. Meanwhile, the axial inclined layout mode of the two-dimensional in-line bent support plate or the three-dimensional bent support plate can further weaken the flow blocking effect in the exhaust diffuser, and further increase the static pressure recovery performance of the exhaust diffuser.
Description
Technical Field
The invention belongs to the technical field of impeller machinery, and particularly relates to a novel exhaust diffuser structure capable of improving aerodynamic performance.
Background
The exhaust diffuser is an important component of a gas turbine, and is generally installed at the downstream of a power turbine, and an internal flow passage of the exhaust diffuser is an expanding passage for performing deceleration and diffusion on gas exhausted by the power turbine. The static pressure recovery capability of the exhaust diffuser can convert part of kinetic energy of the gas at the outlet of the power turbine into outlet static pressure (generally ambient pressure), so that the back pressure at the outlet of the power turbine is reduced, the expansion ratio of the power turbine is increased, and the overall power output of the gas turbine is increased.
With the development of modern industry, the use of gas turbines is more and more extensive, how to improve the operating efficiency of the gas turbines and how to reduce the fuel oil cost become a key problem, nowadays, components such as combustion chambers, compressors and the like have relatively high efficiency, and the economic cost and the technical difficulty for further improving the efficiency of the components are large, but the pneumatic performance of the exhaust diffuser still has a relatively large margin. The static pressure recovery coefficient is a core index for evaluating the pneumatic performance of the exhaust diffuser, and research shows that the overall power output of the gas turbine can be improved by 0.8% when the static pressure recovery coefficient of the exhaust diffuser is improved by 0.1.
All install the backup pad structure in the exhaust diffuser, be used for strengthening the stability of exhaust diffuser casing on the one hand, on the other hand then is as the transport passageway of cooling gas and lubricating oil. The interference of the supporting plate with the air flow in the exhaust diffuser can cause a complex flow state in the exhaust diffuser, and further influences the pneumatic performance of the exhaust diffuser. The supporting plate adopted in the traditional exhaust diffuser is a conventional two-dimensional in-line symmetrical supporting plate, and the layout mode of the supporting plate in the exhaust diffuser adopts a conventional radial layout mode perpendicular to the wall surface of the hub. The support plate structure has the characteristics of simple structure and easiness in processing, but when the support plate structure faces the gas with rotational flow discharged by the upstream power turbine, the gas flow can generate serious flow separation near the support plate, the total pressure loss coefficient of the exhaust diffuser is increased, and the static pressure recovery capability of the exhaust diffuser is reduced. Therefore, the improvement of the configuration of the support plate in the exhaust diffuser is an important means for improving the aerodynamic performance of the exhaust diffuser and has important engineering application value.
Disclosure of Invention
Aiming at the defects that the flow loss is large and the static pressure recovery performance is low in a traditional typical two-dimensional in-line symmetrical supporting plate structure under a large air inlet rotational flow, the invention aims to provide a novel exhaust diffuser structure capable of improving the pneumatic performance, weakening the flow separation near the wall surface of a hub and enhancing the static pressure recovery performance in order to improve the static pressure recovery performance of the exhaust diffuser under the large air inlet rotational flow.
In order to achieve the purpose, the invention adopts the technical scheme that:
the utility model provides a can promote novel exhaust diffuser structure of aerodynamic performance, includes shell body and interior hub, and the inner wall of shell body and the outer wall of interior hub are connected through a plurality of backup pads, and the air current that admits air flows through between the face of adjacent backup pad, the adoption has the airfoil profile type line of camber on the hub wall including the backup pad.
In one embodiment, the support plate adopts an airfoil profile with a curvature on the outer shell wall surface.
In one embodiment, the airfoil profiles of the support plates are the same in a radial direction of the exhaust diffuser, forming a two-dimensional in-line curved support plate.
In one embodiment, the supporting plate adopts a non-camber symmetrical airfoil-shaped profile on the wall surface of the outer shell.
In one embodiment, the plate surface of the support plate is smoothly graded from the inner hub to the outer shell to form a three-dimensional cranked support plate.
In one embodiment, the support plate is inclined in an axial direction of the exhaust diffuser.
In one embodiment, the included angle between the trailing edge line of the support plate and the radial direction of the exhaust diffuser, i.e., the axial inclination angle α, is in a range of 0 < α ≦ 45, and the leading edge line may be parallel to the trailing edge line.
In one embodiment, the chord length c of the support plate is 1/4-1/3 of the axial length L of the exhaust diffuser.
In one embodiment, the leading edge point of the support plate is located at a distance of 1/3-1/2 of the axial length L of the exhaust diffuser from the inlet of the exhaust diffuser, the leading edge point being the intersection of the leading edge line of the support plate and the inner hub of the exhaust diffuser.
In one embodiment, the maximum camber m and the maximum thickness t of the support plate are matched according to the size of the outlet swirl of the upstream power turbine device to achieve optimal aerodynamic performance, wherein the outlet swirl deflection angle β, and the support plate maximum camber m and the maximum camber position p are designed according to the following relations:
β＝Arctan(2m/p)。
when the air inlet prewhirl is large, the support plate with large thickness is suitable, and when the air inlet prewhirl is small, the support plate with small thickness is suitable.
Compared with the prior art, the invention has the beneficial effects that:
the two-dimensional straight-line bent support plate adopted by the invention can keep the simple processing of the support plate, and simultaneously, the coanda effect is utilized to weaken the flow separation near the support plate, reduce the total pressure loss and further improve the static pressure recovery coefficient of the exhaust diffuser.
The three-dimensional bending-twisting-structure supporting plate adopted by the invention can achieve the purpose of weakening the flow separation near the supporting plate by utilizing the characteristic that the wall surface of the hub has the bending degree, meanwhile, the adaptability of the exhaust diffuser to the change of the air inlet rotational flow is enhanced, the static pressure recovery performance of the exhaust diffuser can be improved under different air inlet rotational flows, and the efficient operation capability of the exhaust diffuser under the condition of variable working conditions is enhanced.
When the two-dimensional in-line bent support plate or the three-dimensional bent support plate is arranged in an axial inclined manner, the blocking effect of the support plate on airflow can be further weakened, and the backpressure gradient and the flow loss in the exhaust diffuser are weakened, so that the static pressure recovery coefficient of the exhaust diffuser is increased.
Drawings
FIG. 1 is a three-dimensional schematic view of a conventional typical exhaust diffuser of the present invention, wherein A represents the leading edge point of the support plate and L represents the axial dimension of the exhaust diffuser.
Fig. 2 is a structural diagram of a typical conventional supporting plate of the present invention, wherein t represents the maximum thickness of the supporting plate and C represents the chord length of the supporting plate.
FIG. 3 is a three-dimensional schematic of a two-dimensional in-line curved support plate exhaust diffuser of the present invention.
FIG. 4 is a schematic diagram of a two-dimensional in-line curved support plate configuration of the present invention, wherein t represents the maximum support plate thickness, m represents the maximum support plate curvature, C represents the support plate chord length, and p represents the maximum curvature position.
FIG. 5 is a three-dimensional schematic view of a support plate exhaust diffuser of the present invention having a three-dimensional cranked configuration.
FIG. 6 is a schematic view of a three-dimensional cranked configuration support plate according to the invention.
FIG. 7 is a three-dimensional schematic view of an axially inclined exhaust diffuser of the present invention with a support plate.
Fig. 8 is a schematic diagram of two-dimensional streamline near the inner hub wall surface under the condition of 30-degree air intake deflection of the present invention, wherein (a) is a conventional typical support plate, (b) is a two-dimensional in-line bending support plate, and (c) is a three-dimensional bending configuration support plate.
FIG. 9 is a static pressure recovery coefficient of an exhaust diffuser with a conventional exemplary support plate, a two-dimensional in-line curved support plate, and a three-dimensional curved support plate, under 30 degree inlet deflection conditions in accordance with the present invention.
FIG. 10 is a static pressure recovery coefficient for a conventional exemplary support plate, a two-dimensional in-line curved support plate, and a three-dimensional curved configuration support plate exhaust diffuser for three intake deflection conditions in accordance with the present invention.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention, and the protection scope of the present invention is not limited thereby.
The exhaust diffuser structure comprises an outer shell 2 and an inner hub 3, wherein the inner wall of the outer shell 2 and the outer wall of the inner hub 3 are connected through a plurality of supporting plates, and intake airflow passes through the surfaces of the adjacent supporting plates. Generally, for convenience of manufacturing and stability of air flow, the support plates are uniformly arranged along the circumferential direction, 4-6 support plates are uniformly arranged along the circumferential direction according to the structural strength requirement of the exhaust diffuser, and the support plates are arranged in a manner perpendicular to the hub, that is, the thickness direction of the support plates is perpendicular to the axial direction of the inner hub 3, that is, the air flow direction.
Referring to fig. 1 to 2, in a conventional typical exhaust diffuser structure, a support plate is generally a two-dimensional in-line symmetric support plate 1, that is, a camber-free symmetric airfoil-shaped profile is adopted from a wall surface of an outer casing 2 to a wall surface of an inner hub 3. Its advantage is easy manufacture. However, when the gas has a swirling flow, the gas flow is separated in the vicinity of the support plate, so that the total pressure loss coefficient increases and the static pressure recovery capability decreases.
In the invention, the supporting plate at least adopts the wing-shaped profile line with the camber on the wall surface of the inner hub 3, so that the coanda effect is utilized to reduce flow separation, the flow separation of the airflow with rotational flow discharged by the upstream power turbine is reduced when the airflow flows through the supporting plate, the total pressure loss is reduced, the static pressure recovery performance of the exhaust diffuser is further improved, and the static pressure recovery capability of the exhaust diffuser is enhanced.
On the basis of this, in one embodiment, the supporting plate also adopts an airfoil profile with a curvature on the wall surface of the outer shell 2. And if the airfoil-shaped profile lines of the support plates are the same along the radial direction of the exhaust diffuser, a two-dimensional in-line bent support plate 4 is formed, as shown in fig. 3 to 4. The two-dimensional straight-line bent support plate 4 adapts to air inlet rotational flow by adopting a molded line with a curvature, reduces an air inlet attack angle near the front edge of the support plate, and achieves the purpose of weakening flow separation near the support plate. Meanwhile, the advantages of simple structure and easy processing of the traditional two-dimensional in-line symmetrical support plate are kept. The maximum camber of the molded line can be designed in a matching way according to the rotational flow strength of the airflow at the outlet of the power turbine.
In another embodiment, the support plate still adopts non-camber symmetrical airfoil-shaped profiles on the wall surface of the outer shell 2 to form the three-dimensional bending-torsion-shaped support plate 5, as shown in fig. 5 to 6. Illustratively, the face of the support plate is smoothly tapered from the inner hub 3 to the outer housing 2. The three-dimensional bending-torsion-shaped support plate 5 achieves the purpose of weakening flow separation near the support plate by utilizing the characteristic that the wall surface of the inner hub 3 has bending degree, meanwhile, the adaptability of the exhaust diffuser to the change of the air inlet rotational flow is enhanced, the static pressure recovery performance of the exhaust diffuser can be improved under different air inlet rotational flows, and the efficient operation capability of the exhaust diffuser under the variable working condition is enhanced. The maximum camber of the supporting plate line close to the wall surface of the inner hub 3 can be designed in a matching way according to the rotational flow strength of the airflow at the outlet of the power turbine.
Illustratively, in the present invention, the chord length c of the support plate is generally (1/4-1/3) L according to the structural strength requirement and the axial dimension L of the exhaust diffuser.
The leading edge point of the support plate is at a distance (1/3-1/2) L from the inlet of the exhaust diffuser, where the leading edge point refers to the intersection of the leading edge line of the support plate and the inner hub 3 of the exhaust diffuser.
The maximum bending m and the maximum thickness t of the supporting plate are matched and designed according to the size of the rotational flow at the outlet of the upstream power turbine device, so that the optimal pneumatic performance is achieved.
The outlet swirl deflection angle β, the maximum camber m and the maximum camber position p of the support plate can be designed according to the following relations:
β＝Arctan(2m/p)
maximum thickness t vs. swirl: when the air inlet prewhirl is large, the support plate with large thickness is suitable, and when the air inlet prewhirl is small, the support plate with small thickness is suitable.
The exhaust diffuser of the present invention using the two-dimensional in-line bent support plate 4 and the three-dimensional bent support plate 5 can be generally manufactured by machining after integrally casting an alloy material.
Referring to FIG. 7, in one embodiment, the support plate of the present invention is inclined in the axial direction of the exhaust diffuser. Thereby further weakening the flow blocking effect inside the exhaust diffuser and increasing the static pressure recovery performance of the exhaust diffuser. Illustratively, the included angle between the trailing edge line 6 of the support plate and the radial direction of the exhaust diffuser, i.e., the value range of the axial inclination angle α, is 0 < α ≦ 45 °, and the leading edge line of the support plate may be parallel to the trailing edge line 6.
The technical principle of the invention is as follows:
fig. 8 (a) shows a two-dimensional flow chart of the vicinity of the conventional two-dimensional in-line symmetric support plate 1 when the intake deflection angle is 30 degrees, and as shown in the drawing, when the inlet deflection airflow impacts the front edge of the support plate, a large intake attack angle is formed, which causes a severe flow separation phenomenon to be formed in the vicinity of the two-dimensional in-line symmetric support plate 1, increasing the flow loss, and further causing a reduction in the static pressure recovery coefficient of the exhaust diffuser.
In view of the phenomenon of severe flow separation near the two-dimensional in-line symmetrical support plate 1 when rotational flow exists under the air inlet condition, the two-dimensional in-line bent support plate 4 and the three-dimensional bending-twisting structure support plate 5 fully utilize the coanda effect, so that when fluid in the exhaust diffuser flows across the front edge of the support plate, the fluid can better adhere to the surface of the support plate to flow, the flow separation near the support plate is weakened, and the static pressure recovery coefficient of the exhaust diffuser is further increased. Fig. 8 (b) and (c) show two-dimensional flow charts of the two-dimensional in-line bent support plate 4 and the three-dimensional bent-configuration support plate 5, which are designed to be matched according to the intake deflection angle at 30 degrees, in the vicinity of the inner hub 3. As shown, there is little separation of the fluid near the two-dimensional in-line bent support plate 4 and the three-dimensional twisted configuration support plate 5, which reduces flow losses in the exhaust diffuser.
Referring to fig. 9, when the intake deflection angle is 30 degrees, the static pressure recovery coefficient of the conventional typical exhaust diffuser is 0.2804, and the static pressure recovery coefficient of the two-dimensional straight-line bent support plate exhaust diffuser which is designed to match the intake deflection angle is 0.3182, which is relatively increased by 13.5%. The static pressure recovery coefficient of the three-dimensional bending configuration support plate exhaust diffuser which is designed according to the air inlet deflection angle in a matching mode is 0.3292, and the static pressure recovery coefficient is relatively increased by 17%.
Referring to fig. 10, during the actual operation of the gas turbine, the operation condition of the gas turbine as a whole may change due to the adjustment of the operation state. The change of the rotating speed of the power turbine can cause the strength of the inlet rotational flow of the outlet of the power turbine, namely the inlet of the exhaust diffuser, to change. Fig. 10 shows the influence of the two-dimensional in-line symmetrical support plate, the two-dimensional in-line bent support plate 4 and the three-dimensional bent support plate 4 designed to match when the air deflection angle is 30 degrees, on the static pressure recovery coefficient of the exhaust diffuser when the air inlet deflection is 24 degrees, 30 degrees (design condition) and 42 degrees, respectively. As shown in the figure, when the inlet deflection angle is greater than 30 degrees (design condition), the two-dimensional in-line bent support plate 4 and the three-dimensional bent support plate 5 can still improve the static pressure recovery coefficient of the exhaust diffuser compared with the conventional typical two-dimensional in-line symmetrical support plate 1. When the air inlet deflection angle is smaller than 30 degrees (design working condition), compared with the traditional typical two-dimensional in-line symmetrical support plate 1, the static pressure recovery coefficient of the two-dimensional in-line bent support plate exhaust diffuser is slightly reduced, and the static pressure recovery coefficient of the three-dimensional bent support plate exhaust diffuser is still slightly improved, which shows that the three-dimensional bent support plate 5 can still run efficiently under the condition of variable working conditions.
Claims (10)
1. The utility model provides a can promote novel exhaust diffuser structure of aerodynamic performance, includes shell body (2) and interior hub (3), and the inner wall of shell body (2) and the outer wall of interior hub (3) are connected through a plurality of backup pads, and the air current that admits air flows through between the face of adjacent backup pad, its characterized in that, the backup pad adopts the airfoil profile type line that has the camber on interior hub (3) wall.
2. The new structure of an exhaust diffuser able to improve aerodynamic performance according to claim 1, characterized in that said support plate uses airfoil shaped profiles with camber on the outer casing (2) wall.
3. Novel exhaust diffuser structure capable of improving aerodynamic performance according to claim 1 or 2, characterized in that the profile of the support plates is the same in the radial direction of the exhaust diffuser, forming a two-dimensional in-line curved support plate (4).
4. The new structure of an exhaust diffuser able to improve aerodynamic performance according to claim 1, characterized in that said support plate uses a non-camber symmetrical airfoil profile on the outer casing (2) wall.
5. The new structure of an exhaust diffuser capable of improving aerodynamic performance according to claim 4, characterized in that the plate surface of the support plate is smoothly graded from the inner hub (3) to the outer casing (2) to form a support plate (5) with a three-dimensional twisted configuration.
6. The novel exhaust diffuser structure capable of improving aerodynamic performance according to any one of claims 1 to 5, wherein the support plate is inclined in an axial direction of the exhaust diffuser.
7. The novel exhaust diffuser structure capable of improving aerodynamic performance according to claim 6, wherein an included angle between the trailing edge line (6) of the support plate and the radial direction of the exhaust diffuser, i.e., an axial inclination angle α, is in a range of 0 < α ≦ 45 °.
8. The novel exhaust diffuser structure capable of improving aerodynamic performance according to any one of claims 1 to 5, wherein the chord length c of the support plate is 1/4-1/3 of the axial length L of the exhaust diffuser.
9. A novel exhaust diffuser structure capable of improving aerodynamic performance according to any one of claims 1 to 5, characterized in that the leading edge point of the support plate is located at a distance of 1/3-1/2 of the axial length L of the exhaust diffuser from the inlet of the exhaust diffuser, and the leading edge point is the intersection point of the leading edge line of the support plate and the inner hub (3) of the exhaust diffuser.
10. The novel exhaust diffuser structure capable of improving aerodynamic performance according to any one of claims 1 to 5, wherein the maximum camber m and the maximum thickness t of the support plate are designed to match the size of the outlet swirl of the upstream power turbine device to achieve the optimal aerodynamic performance, wherein the outlet swirl deflection angle β, the maximum camber m and the maximum camber position p of the support plate are designed according to the following relations:
β＝Arctan(2m/p)。
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856717A (en) * | 2022-06-02 | 2022-08-05 | 西安交通大学 | Novel exhaust diffuser structure with splitter plate and capable of enhancing pneumatic performance |
| CN118532716A (en) * | 2024-07-25 | 2024-08-23 | 中国空气动力研究与发展中心空天技术研究所 | Combined diffuser for centripetal air intake of combustion chamber and design method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120198810A1 (en) * | 2011-02-04 | 2012-08-09 | General Electric Company, A New York Corporation | Strut airfoil design for low solidity exhaust gas diffuser |
| EP2559850A1 (en) * | 2011-08-19 | 2013-02-20 | Siemens Aktiengesellschaft | Exhaust diffuser and method for manufacturing an exhaust diffuser |
| US20140026999A1 (en) * | 2012-07-25 | 2014-01-30 | Solar Turbines Incorporated | Exhaust diffuser for a gas turbine engine having curved and offset struts |
| CN108644152A (en) * | 2018-04-04 | 2018-10-12 | 中国航发湖南动力机械研究所 | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor |
| CN113623027A (en) * | 2021-09-18 | 2021-11-09 | 西安交通大学 | Experimental table for measuring aerodynamic performance of exhaust diffuser capable of carrying out steady-state and transition-state experimental measurement |
-
2021
- 2021-12-03 CN CN202111468432.1A patent/CN114151195A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120198810A1 (en) * | 2011-02-04 | 2012-08-09 | General Electric Company, A New York Corporation | Strut airfoil design for low solidity exhaust gas diffuser |
| EP2559850A1 (en) * | 2011-08-19 | 2013-02-20 | Siemens Aktiengesellschaft | Exhaust diffuser and method for manufacturing an exhaust diffuser |
| US20140026999A1 (en) * | 2012-07-25 | 2014-01-30 | Solar Turbines Incorporated | Exhaust diffuser for a gas turbine engine having curved and offset struts |
| CN108644152A (en) * | 2018-04-04 | 2018-10-12 | 中国航发湖南动力机械研究所 | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor |
| CN113623027A (en) * | 2021-09-18 | 2021-11-09 | 西安交通大学 | Experimental table for measuring aerodynamic performance of exhaust diffuser capable of carrying out steady-state and transition-state experimental measurement |
Non-Patent Citations (1)
| Title |
|---|
| 董雨轩、李志刚、李军: "支撑板型线和径向倾斜设计对燃气轮机排气扩压器气动性能的影响" * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856717A (en) * | 2022-06-02 | 2022-08-05 | 西安交通大学 | Novel exhaust diffuser structure with splitter plate and capable of enhancing pneumatic performance |
| CN118532716A (en) * | 2024-07-25 | 2024-08-23 | 中国空气动力研究与发展中心空天技术研究所 | Combined diffuser for centripetal air intake of combustion chamber and design method thereof |
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