CN105715316B - A kind of simple exhaust frame of the band support plate of falling zigzag - Google Patents
A kind of simple exhaust frame of the band support plate of falling zigzag Download PDFInfo
- Publication number
- CN105715316B CN105715316B CN201610053192.1A CN201610053192A CN105715316B CN 105715316 B CN105715316 B CN 105715316B CN 201610053192 A CN201610053192 A CN 201610053192A CN 105715316 B CN105715316 B CN 105715316B
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- China
- Prior art keywords
- support plate
- exhaust frame
- falling
- inner ring
- outer shroud
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Classifications
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Abstract
The present invention relates to a kind of simple exhaust frame of the band support plate of falling zigzag, including：Inner ring, outer shroud and along the circumferential direction uniform multiple support plates, the support plate are located between inner ring and outer shroud, so as to constitute the annular waste air duct of aero-engine, it is characterised in that：The support plate is that the band support plate of falling zigzag, i.e. support plate are used similar to the design of falling Z-shaped, and annular fuel gas passage is constituted between inner ring, outer shroud and the support plate of falling zigzag.The present invention can effectively alleviate the thermal stress of exhaust frame, simplify exhaust frame structure design, reduce production cost, shorten the process-cycle, and lightweight, reliability is high；The loss of exhaust frame pressure at expulsion is small, can improve level of engine performance；Have a wide range of application, in can be widely applied to various small gas turbine shaft generators, auxiliary power unit or starter.
Description
Technical field
The present invention relates to a kind of exhaust frame, and in particular to a kind of simple exhaust frame of the band support plate of falling zigzag.
Background technology
The present invention relates to the simple exhaust frame that aero-engine is used.The exhaust frame is arranged on aero-turbine
Outlet, is mainly made up of in structure outer shroud, inner ring and along the circumferential direction uniform multiple support plates etc., and its major function is and exhaust
Framework outer shroud, inner ring form blast tube, and organize turbine outlet combustion gas to enter air with direction at the appropriate speed.Such
In type exhaust frame, support plate mainly plays connection inner and outer rings as important component, increases the effect of exhaust frame rigidity.
Exhaust frame is the component of turbine outlet combustion gas discharge, and turbine outlet fuel gas temperature is higher, typically 500~
600 °C or so, its temperature field is uneven, while there is the alternation procedure of cold cycling, exhaust frame using process in engine
Inner ring, outer annular strain are inconsistent, easily crack and deform under the restriction effect of support plate.Therefore, for exhaust frame
How speech, discharged or relief of thermal stress by preferable structure design means, improves the life and reliability of part, is that structure sets
The thorny problem that timing must take into consideration.
Additionally, turbine outlet combustion gas stream generally deviates axial flowing with certain pre-swirl angle, and radially
Pre-swirl angle there is also certain inhomogeneities.Therefore, if the support plate design in exhaust frame arrange it is unreasonable if, will be
The larger angle of attack is produced near its leading edge so that the air-flow for flowing through branch plate surface produces large area to separate, in exhaust frame expert
Into the secondary flow opposite with main flow direction, exhaust frame pitot loss is caused to sharply increase, exhaust is not smooth, and then influence is started
Machine performance.
Traditional exhaust frame generally requires the structure design of taking some complicated for relief of thermal stress, such as in inner ring or outer
Ring uses back bending structure design, the part of the class formation cannot punch forming, casting, process-cycle, difficult processing need to be used
Degree and processing cost have increase by a relatively large margin；Its support plate typically uses simple prismatic blade, it is difficult to adapt to turbine outlet air-flow
Non-uniformity in radial position, cause exhaust passage interior air-flow flow separation by a relatively large margin occur along branch plate surface, so as to cause row
Gas loss increases, and engine performance declines.
The content of the invention
Technology solve problem of the invention：Overcome the deficiencies in the prior art, a kind of simple exhaust frame of the band support plate of falling zigzag
Frame, effectively alleviates the thermal stress of exhaust frame, simplifies the structure of exhaust frame, mitigates weight, improves reliability, reduces difficult processing
Degree and processing cost, while exhaust pitot loss can be reduced, improve engine performance.
The technology of the present invention solution：A kind of simple exhaust frame of the band support plate of falling zigzag.The exhaust frame is by interior
Ring, outer shroud and the along the circumferential direction uniform multiple support plate of falling zigzag composition.Ring is constituted between inner ring, outer shroud and the support plate of falling zigzag
Shape blast tube, the support plate of falling zigzag is welded between the outer shroud and inner ring.The outer shroud and inner ring runner line can be straight line
Or curve.The support plate of falling zigzag is different from traditional symmetrical airfoil prismatic blade, is designed like in the shape of falling zigzag.
The exhaust frame inner ring and outer shroud during engine use because thermal deformation it is inconsistent produced by thermal stress by falling Z-shaped
Shape support plate is alleviated or is eliminated.
The exhaust frame support plate of falling zigzag is radially broadly divided into three sections：It is welded on the support plate upper half on outer shroud
Section and the support plate lower semisection being welded in inner ring, and the stage casing parallel with engine axis.The support plate of the falling zigzag upper semisection
Radially each cross sectional shape is identical, and radially each cross sectional shape of support plate lower semisection is also identical.The support plate of falling zigzag
Upper semisection, lower semisection and engine axis are respectively present angle α 1, angle α 2, and the angles of α 1 and α 2 are differed.The angle value of α 1 is near
Like with the annular air-flow path upper part inlet at match flowing the average value of pre-swirl angle；The angle value of α 2 approximately with
Annular air-flow path the latter half porch matches flowing the average value of pre-swirl angle, makes the combustion gas can by angle automatching
It is smooth to flow through exhaust frame, flow separation is not produced, the pressure loss is small.
The exhaust frame inner ring, outer shroud, the support plate of falling Z-shaped can individually punch forming, the support plate of falling Z-shaped is welded in inner ring
Between outer shroud.
The exhaust frame inner ring, the runner line of outer shroud are straight line or curve.
Present invention advantage compared with prior art is：
（1）Traditional exhaust frame generally requires the structure design of taking some complicated for relief of thermal stress, such as in inner ring
Or outer shroud uses back bending structure design, the part of the class formation cannot punch forming, need to use casting, difficulty of processing and add
Work cost is increased considerably.Exhaust frame inner ring of the present invention, outer shroud and support plate can punch forming, and by the support plate of falling Z-shaped
The thermal stress of exhaust frame is effectively alleviated in design, simplifies exhaust frame structure design, reduces low production cost, shortens processing week
Phase, and lightweight, reliability is high；
（2）The support plate of traditional exhaust frame typically uses simple prismatic blade, due to the radial distribution of turbine outlet air-flow
Uneven, this support plate design can cause exhaust passage interior air-flow that flow separation occurs along support plate surface portion or all, so that
Causing discharge loss increases, and engine performance declines.The support plate of falling zigzag upper semisection of the invention, lower semisection and engine axis point
Not there is angle α 1, angle α 2, can preferably adapt to the radially non-uniform of turbine outlet air-flow, the loss of exhaust frame pressure at expulsion
It is small, level of engine performance can be improved；
（3）Have a wide range of application, can be widely applied to various small gas turbine shaft generators, auxiliary power unit or starting
In machine.
Brief description of the drawings
Fig. 1 for the present invention in exhaust frame in shaft gas turbine engine scheme of installation；
Fig. 2 is conventional exhaust framework fragmentary, perspective view；
Fig. 3 is the exhaust frame fragmentary, perspective view of the band support plate of falling zigzag of the invention；
Fig. 4 is the support plate of the falling zigzag side view in exhaust frame of the present invention；
Fig. 5 is that the support plate of falling zigzag of exhaust frame in the present invention faces cut away view；
Fig. 6 is that the support plate of falling zigzag of exhaust frame in the present invention looks up cut away view；
Fig. 7 is that the support plate of falling zigzag of exhaust frame in the present invention overlooks cut away view.
1. exhaust frame outer shroud, 2. exhaust frame inner ring, the 3. support plate of falling zigzag, the 4. support plate of falling zigzag upper semisection 5. falls Z
Font support plate stage casing, the 6. support plate of falling zigzag lower semisection, 7. engine axis, 8. combustion gas, 9. allotment plate, 10. exhaust frame back bending
Structure outer shroud, 11. turbines, 12. exhaust frames.
Specific embodiment
As shown in figure 1, after exhaust frame of the invention 12 is arranged on the turbine 11 of shaft gas turbine engine, through turbine 11
High-temperature fuel gas 8 after acting discharge engine by the annular air-flow path between exhaust frame outer shroud 1 and exhaust frame inner ring 2
12.The turbine 11 of aero-engine can be single-stage axial turbine, Double-Stage Axial Flow Water turbine or centripetal turbine, aero-engine
Turbine 11 and exhaust frame 12 be loop configuration, it is symmetrical around engine axis 7.
As shown in Fig. 2 conventional exhaust framework fragmentary, perspective view, conventional exhaust framework by exhaust frame inner ring 2, allotment plate 9,
Exhaust frame back bending structure outer shroud 10 is constituted.The exhaust frame inner ring 2, exhaust frame back bending structure outer shroud 10 and allotment plate 9 it
Between constitute annular air-flow path, exhaust back pressure is usually utilized to greatest extent, reduce exhaust airstream speed, annular air-flow path is
Gradually expand, i.e., entrance circulation area is less than outlet stream area.Conventional exhaust framework on outer shroud by using back bending knot
Structure design is to eliminate or relief of thermal stress, and the blade profile of its allotment plate 9 each section blade profile from blade root to blade tip is completely the same.
Fig. 3 gives an example of the simple exhaust frame of the band support plate of falling zigzag of the present invention, by exhaust frame
Outer shroud 1, the support plate of falling zigzag 3, exhaust frame inner ring 2 are constituted.Exhaust frame inner ring 2 of the present invention, exhaust frame outer shroud 1, fall
Z-shaped support plate 3 can individually punch forming, the described multiple support plate of falling zigzag 3 (details are referring to Fig. 4-Fig. 7) is along the circumferential direction equal
Even is welded between exhaust frame inner ring 2 and exhaust frame outer shroud 1.The exhaust frame inner ring 2, exhaust frame outer shroud 1 and
Annular air-flow path is constituted between the support plate of falling zigzag 3, exhaust back pressure is usually utilized to greatest extent, reduce exhaust airstream speed,
Annular air-flow path is gradually expanded, i.e., entrance circulation area is less than outlet stream area, its exhaust frame inner ring 2, exhaust
The runner line of framework outer shroud 1 can be straight line or curve.
As shown in figs. 4-7, the support plate of falling zigzag 3 by the support plate of the falling zigzag upper semisection 4 that couples with exhaust frame outer shroud 1 and
The parallel support plate of the falling zigzag stage casing 5 of engine axis 7 and 6 groups of the support plate of the falling zigzag lower semisection coupled with exhaust frame inner ring 2
Into.Relative to traditional design method in inner ring or outer ring use back bending structure, using the support plate of falling zigzag design alleviated or
Eliminate due to inner ring, the thermal stress of the inconsistent generation of outer annular strain, can greatly simplify design of part complexity, the row of alleviating
Air frame frame total quality, reduces difficulty of processing and production cost.
Additionally, it can be clearly seen that the support plate of falling zigzag upper semisection 4, the support plate of falling zigzag lower semisection 6 from Fig. 4-Fig. 7
Angle α 1, α 2 with engine axis are differed, and α 1 is designed as being approximately equal to the circular passage entrance 50%-100% of exhaust frame 12
The highly average value of the air-flow pre-swirl angle at place, α 2 is designed as being approximately equal to the air-flow that circular passage entrance 0%-50% highly locates and prewhirls
The average value at angle.The support plate of exhaust frame 12 is designed using this, is adapted to the inhomogeneities that air-flow pre-swirl angle is radially gone up,
Make exhaust more smooth, and taken into account non-setting due to air-flow separation caused by the angle of attack in most regions in reduction circular passage
Under meter working condition, so as to reduce exhaust pitot loss, engine performance is improved.
It is of the present invention with zigzag support plate low cost simple non-bearing exhaust frame processing after carried out blowing test,
And engine completion overall performance test and endurence test are assembled, as a result show, using the row with zigzag support plate of the present invention
Air frame frame its processing cost is only the 62% of conventionally employed back bending structure and allotment plate exhaust frame cost, while can obviously reduce
Exhaust pitot loss, improves engine performance, and with preferable life-span and reliability.
Above example is provided just for the sake of the description purpose of the present invention, and is not intended to limit the scope of the present invention.This
The scope of invention is defined by the following claims.The various equivalents that do not depart from spirit and principles of the present invention and make and repair
Change, all should cover within the scope of the present invention.
Claims (3)
1. a kind of simple exhaust frame of the band support plate of falling zigzag, including：Inner ring, outer shroud and along the circumferential direction uniform multiple
Support plate, the support plate is located between inner ring and outer shroud, so as to constitute the annular waste air duct of aero-engine, it is characterised in that：
The support plate is that the support plate of falling zigzag, i.e. support plate are used similar to the design of falling Z-shaped, between inner ring, outer shroud and the support plate of falling zigzag
Constitute annular fuel gas passage；
The support plate of falling zigzag is radially divided into upper semisection, lower semisection and stage casing, and stage casing therein is put down with engine axis
OK, radially each cross sectional shape of upper semisection is identical, and radially each cross sectional shape of lower semisection is identical；
The upper semisection of the support plate of falling zigzag, lower semisection and engine axis are respectively present angle α 1, angle α 2, α 1, the angles of α 2
Differ, α 1 is designed as being approximately equal to the average of the air-flow pre-swirl angle that exhaust frame circular passage entrance 50%-100% highly locates
Value, α 2 is designed as being approximately equal to the average value of the air-flow pre-swirl angle that circular passage entrance 0%-50% highly locates.
2. the simple exhaust frame of the band support plate of falling zigzag according to claim 1, it is characterised in that：The exhaust frame
The independent punch forming of inner ring, outer shroud, the support plate of falling Z-shaped, the support plate of falling Z-shaped is welded between inner ring and outer shroud.
3. the simple exhaust frame of the band support plate of falling zigzag according to claim 1, it is characterised in that：The exhaust frame
Inner ring, the runner line of outer shroud are straight line or curve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610053192.1A CN105715316B (en) | 2016-01-26 | 2016-01-26 | A kind of simple exhaust frame of the band support plate of falling zigzag |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610053192.1A CN105715316B (en) | 2016-01-26 | 2016-01-26 | A kind of simple exhaust frame of the band support plate of falling zigzag |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105715316A CN105715316A (en) | 2016-06-29 |
| CN105715316B true CN105715316B (en) | 2017-06-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610053192.1A Active CN105715316B (en) | 2016-01-26 | 2016-01-26 | A kind of simple exhaust frame of the band support plate of falling zigzag |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1550649A (en) * | 2003-05-16 | 2004-12-01 | �����ع�ҵ��ʽ���� | Exhaust diffuser for axial-flow turbine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6969230B2 (en) * | 2002-12-17 | 2005-11-29 | General Electric Company | Venturi outlet turbine airfoil |
| FR2865002B1 (en) * | 2004-01-12 | 2006-05-05 | Snecma Moteurs | DOUBLE FLOW TURBOREACTOR COMPRISING A SERVITUDE DISTRIBUTION SUPPORT AND THE SERVITUDE DISTRIBUTION SUPPORT. |
| US7625182B2 (en) * | 2006-09-05 | 2009-12-01 | Pratt & Whitney Canada Corp. | Turbine exhaust strut airfoil and gas path profile |
| EP2863021B1 (en) * | 2008-02-27 | 2016-05-25 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine support structure |
| FR2933130B1 (en) * | 2008-06-25 | 2012-02-24 | Snecma | STRUCTURAL CASING FOR TURBOMACHINE |
| CN102157320B (en) * | 2011-03-08 | 2012-11-28 | 李梦琪 | Exhaust framing device |
| US9422864B2 (en) * | 2012-12-20 | 2016-08-23 | General Electric Company | Staggered double row, slotted airfoil design for gas turbine exhaust frame |
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2016
- 2016-01-26 CN CN201610053192.1A patent/CN105715316B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1550649A (en) * | 2003-05-16 | 2004-12-01 | �����ع�ҵ��ʽ���� | Exhaust diffuser for axial-flow turbine |
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| CN105715316A (en) | 2016-06-29 |
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