CN208518718U - Aerodynamics rectification part, exhaust diffuser and the gas turbine of pillar for exhaust diffuser - Google Patents
Aerodynamics rectification part, exhaust diffuser and the gas turbine of pillar for exhaust diffuser Download PDFInfo
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- CN208518718U CN208518718U CN201820683490.3U CN201820683490U CN208518718U CN 208518718 U CN208518718 U CN 208518718U CN 201820683490 U CN201820683490 U CN 201820683490U CN 208518718 U CN208518718 U CN 208518718U
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- exhaust diffuser
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Abstract
The embodiment of solution described herein is related to a kind of aerodynamics rectification part of pillar for exhaust diffuser.Aerodynamics rectification part includes: leading edge portion, it is exposed to the air-flow of upstream blade arrival, aerodynamics rectification part blades adjacent on the axial direction of exhaust diffuser is arranged, it is characterized in that, leading edge portion extends to inner end from the outer end of aerodynamics rectification part in radial directions, and wherein leading edge portion is curved in radial directions.
Description
Technical field
The embodiment of the present invention relates generally to gas turbine, more particularly relates to the sky of the pillar of exhaust diffuser
Aerodynamics rectification part, includes the exhaust diffuser of aerodynamics rectification part, and includes the combustion gas of exhaust diffuser
Turbine.
Background technique
Aerodynamics rectification part is arranged in behind multistage gas turbine afterbody blade, and protect Spanning Star with
Make it from hot waste gas.In order to reduce air flow losses and in order to ensure passing through the low-loss air-flow of exhaust diffuser, sky is needed
The aerodynamic design of the optimization of aerodynamics rectification part, to realize its high efficiency and good performance.
Currently, a main challenge is to be adapted to the geometry of aerodynamics rectification part for fractional load
Various design points in range.Since the outflow angle of the afterbody turbine rotor under fractional load may be partially offset from
Design point, and the geometry of aerodynamics rectification part is immutable, this will lead to fractional load air-flow with rectification
The leading edge in portion is generated with side surface after interacting and biggish is separated.As a result, the efficiency of entire machine reduces.Separately
Outside, this aeromechanics exciting for also resulting in the shell as caused by increased incidence angle.
A kind of exhaust diffuser is proposed in EP2410139A1.The exhaust diffuser includes permeable inner wall, this is interior
Wall influences the air-flow in inner wall area after air flow through air dynamics rectification part, so that the flowing in diffuser be made to damage
Consumption minimizes.However, the disclosure is not related to any modification to the geometry of aerodynamics rectification part, therefore do not solve yet
The problem of certainly the aerodynamics interaction between air-flow and aerodynamics rectification part may deteriorate.
Summary of the invention
Embodiment of the disclosure provides a kind of aerodynamics rectification part of optimization for exhaust diffuser.
In a first aspect, providing a kind of aerodynamics rectification part for exhaust diffuser.Aerodynamics rectification
Portion includes: the leading edge portion for being exposed to the air-flow of upstream blade arrival, axis of the aerodynamics rectification part in exhaust diffuser
Blades adjacent is arranged on direction, which is characterized in that leading edge portion is in radial directions from the outer end of aerodynamics rectification part
Extend to inner end, and the leading edge portion be in radial directions it is curved, formed at the flow path of exhaust airstream as a result,
Recess portion.
According to various embodiments of the present invention, the three-dimensional surface at recess portion and leading edge portion formed in the direction of the air flow
The air-flow under various part-load conditions with various outflow angles is allowed to pass through with low-loss.Diffuser can be as a result,
It is more efficiently run in wider load range.
In addition, may be implemented preferably empty between air-flow and curved surface using appropriately designed and optimization curved surface
Aerodynamics interaction, which improve the performances of diffuser, such as improve efficiency, and at the same time reducing swashing for shell
Vibration.
In some embodiments, curved leading edge portion includes the first profile song for being configured to cubic Bézier curve
Line, first profile curve intersect with outer end and inner end.
In some embodiments, curved leading edge portion includes being configured to parabolical first profile curve, the parabolic
Line has the symmetry axis extended in the axial direction, and first profile curve intersects with outer end and inner end.
In some embodiments, first profile curve is formed so that from outer end to parabolical symmetry axis in radial direction
First distance on direction is less than the second distance in radial directions from inner end to parabolical symmetry axis.
In some embodiments, first profile curve is formed so that from outer end to parabolical symmetry axis in radial direction
First distance on direction is equal to the second distance in radial directions from inner end to parabolical symmetry axis.
In some embodiments, first profile curve is formed so that from outer end to parabolical symmetry axis in radial direction
First distance on direction is greater than the second distance in radial directions from inner end to parabolical symmetry axis.
In some embodiments, aerodynamics rectification part has the center for including in the plane being perpendicularly to the radial direction
The profile of line, wherein the center line is straight line and is aligned with axial direction.
In second aspect, a kind of exhaust diffuser is provided.The exhaust diffuser includes: the first aspect according to the disclosure
Multiple aerodynamics rectification parts；And multiple aerodynamics are attached at the inner end of multiple aerodynamics rectification parts
The wheel hub of rectification part.
In some embodiments, multiple aerodynamics rectification parts are uniformly distributed on the circumferencial direction of wheel hub.
In the third aspect, a kind of gas turbine is provided.Gas turbine includes the exhaust according to the second aspect of the disclosure
Diffuser.
It will become apparent that, this appropriately designed aerodynamics rectification part, diffusion are utilized by following embodiment
Device can more efficiently be run in wider load range.Further, since improved aerodynamics interacts, construct
Three-dimensional bending surface make steady air current, it reduce potential shell-induced vibration and provide improved system performance, especially
It is when running at a part-load condition.In addition, aerodynamics rectification part does not need additional component, this is easily fabricated and drops
Low overall cost.
It should be appreciated that the content of present invention is not intended to the crucial of the embodiment of mark solution described herein or substantially special
Sign, is intended to be used to limit the range of solution described herein.Pass through following description, solution described herein
Other features will become prone to understand.
Detailed description of the invention
By the more detailed description of the example embodiment of the technical solution described herein in conjunction with attached drawing, skill described herein
Above and other purposes, the feature and advantage of art scheme will be apparent, wherein showing in solution described herein
In example embodiment, identical appended drawing reference usually indicates identical component.
Fig. 1 is the perspective view according to the exhaust diffuser of the embodiment of the technical solution of disclosure description；
Fig. 2 schematically illustrates the aerodynamics rectification of one embodiment of the technical solution according to disclosure description
The side view in portion；
The aerodynamics that Fig. 3 A schematically illustrates one embodiment of the technical solution according to disclosure description is whole
The side view in stream portion；
The aerodynamics that Fig. 3 B schematically illustrates one embodiment of the technical solution according to disclosure description is whole
The side view in stream portion；
The aerodynamics that Fig. 3 C schematically illustrates one embodiment of the technical solution according to disclosure description is whole
The side view in stream portion；
Fig. 4 A schematically illustrates spreading for being directed to for one embodiment of the technical solution according to disclosure description
Device efficiency optimizes parabolical design point；
Fig. 4 B be schematically illustrated one embodiment of the technical solution according to disclosure description for for diffuser
Efficiency optimizes the design point of quadratic B é zier curve；And
Fig. 5 schematically illustrates the aerodynamics rectification of one embodiment of the technical solution according to disclosure description
The longitudinal section view in portion.
Specific embodiment
Solution described herein is discussed now with reference to several example embodiments.It should be appreciated that these embodiments
Merely for make those skilled in the art can better understand that and therefore realize techniques described herein scheme purpose begged for
By without the range proposition any restrictions to technical solution.
As it is used herein, term " includes " and its modification should be read as meaning opening art " including but not limited to "
Language.Term "based" should be read as " being at least partially based on ".Term " one embodiment " and " embodiment " should be read as " at least
One embodiment ".Term " another embodiment " should be read as " at least one other embodiment ".Term " first ", " the
Two " etc. may refer to similar and different object.Others definition, specific and implicit, it can be included herein below.It removes
Non- context explicitly points out, and otherwise the definition of term is consistent throughout the specification.
Fig. 1 schematically illustrates exhaust diffuser 10 according to various embodiments of the present disclosure.As shown, exhaust is expanded
Dissipating device 10 includes multiple aerodynamics rectification parts extend on radial direction R, for protecting Spanning Star from hot waste gas
1, and it is attached at the inner end of aerodynamics rectification part 1 wheel hub 3 of aerodynamics rectification part 1.In this example, empty
Aerodynamics rectification part 1 is uniformly distributed on the circumferential direction C of wheel hub 3.Wheel hub 3 is arranged in the axial direction of exhaust diffuser 10
Behind a series of afterbody rotor of rotors on X.In this way, aerodynamics rectification part 1 is axially square
It is arranged to adjacent with the blade 2 of the last one rotor to X and is substantially aligned with.
Aerodynamics rectification part 1 includes the outer end 13 and inner end 14 for wheel hub 3 on radial direction R.?
This, outer end 13 can also be known as tip, and inner end 14 can also be known as hub end.Aerodynamics rectification part 1 further includes leading edge potion
11 (" leading edge " can also be known as below) and rear edge part opposite with leading edge portion 11 on X in the axial direction are divided (may be used also below
To be known as " rear ").Leading edge can be defined as the air-flow for being exposed to the guidance of upstream blade 2 and contact foremost
Edge, and rear can be defined as trailing edge, be reconsolidated by the air-flow that leading edge separates in the rear.In addition, leading edge via
Smooth side surface is transitioned into rear.In some embodiments, the shape of side surface can be adjusted based on aerodynamics and
Optimization, to generate the streamline for being adapted to side surface configuration, to reduce air flow losses.
As discussed above, it is generally the case that the shape/geometry of aerodynamics rectification part is substantially only for combustion
Operation under the full load of air turbine is designed and optimizes.However, needing to run whirlpool under fractional load in some cases
When wheel, potential problem is to guide air-flow that may deviate designed outflow angle from the outflow angle of the last one blade 2.This
The deterioration that will lead to the aerodynamics interaction between air-flow and aerodynamics rectification part 1, because when having deflecting angle
After the fractional load air-flow and aerodynamics rectification part 1 of degree interact, this fractional load air-flow will be with side table
Face has larger amount of separation, which in turn reduces the efficiency of diffuser and generates the exciting of shell.
In order at least solve this problem in fractional load emerged in operation, in accordance with an embodiment of the present disclosure, leading edge potion
Points 11 be configured on radial direction R be it is curved, to form curved surface 12, which extends to from outer end 13
Inner end 14.In this way, when from side surface, recess portion 15 is formd.In this way, enable deviate off-gas flows 30
It is enough that leading edge portion 11 is passed through with improved aerodynamics interaction.In other words, recess portion 15 can slow down or reduce by (as above
Discuss) separation of air-flow caused by fractional load air-flow.
When turbine is run under fractional load, the recess portion 15 of formation and the three-dimensional surface 12 formed are provided for sky jointly
The relatively broad range of robustness of the outflow angle of air-flow 30.It in other words, can since better aerodynamics interacts
Allow to have the air-flow of different angle with low-loss by leading edge portion 11 in the case where different fractional loads is horizontal, this then improves
The performance of diffuser and the exciting for reducing shell.
In addition, in order to make diffuser 10 adapt to service condition as much as possible, in some embodiments, curved surface 12
Shape/geometry can for example optimize for the efficiency of diffuser.
As an example, the contour curve 121 of curved surface 12 (hereafter may be used also in some embodiments as illustrated in Figure 2
With referred to as first profile curve) reflect the span on radial direction R relative to the various leading edge locus on axial direction X
Distribution.The contour curve 121 may be constructed such that cubic Bézier curve (or three rank Bézier curves), cubic Bézier curve
Intersect respectively at point A and point B with outer end 13 and inner end 14.
Bézier curve is widely used in simulating smoothed curve in computer graphical or mathematics.In this case, it takes
Certainly according to order of a curve number, the shape of curve can optimize by adjusting several control points, this realizes flexible curve
Design.For example, cubic Bézier curve can be according to two terminal As and B and two other intermediate point in optimization process
The position of (not shown) --- i.e. four points --- optimizes.Certainly, the Bézier curve with higher order is also possible.
In some embodiments, cubic Bézier curve can be optimized in single optimization process all there are four points.It is standby
Selection of land, in order to avoid heavier computation burden and/or in order to obtain with the acceptable of resource consumption good compromise as a result, at it
In his embodiment, more simplified method can be used to optimize curved surface 12.Moreover, according to the discovery and observation of inventor,
For example, the optimization that simplifies with reduced design point number is still enough to realize the performance of optimization for majority of case.
Therefore, in alternative embodiment as shown in Figure 3A, the first profile curve 121 of curved surface 12 can be constructed
For quadratic B é zier curve (or second order Bézier curve).In this case, the number of design point can be reduced to three.From
From the point of view of mathematical angle, quadratic B é zier curve is equivalent to parabola (being referred to as quadratic polynomial curve).
As shown, parabola has the symmetry axis 18 extended on X in the axial direction.That is, parabola has court
The parabola opening of direction X in the axial direction.In addition, first profile curve 121 in the mode similar with shown in Fig. 2 in the first point A and
Intersect respectively at second point B with outer end 13 and inner end 14.
Therefore, the position that the adjustment of parabolical shape can be based at least partially on mobile parabolical symmetry axis 18 is come
It executes.In embodiment as shown in Figure 3A, first profile curve 121 be may be formed so that from outer end 13 to parabolical
The first distance H1 on radial direction R of symmetry axis 18 is less than from inner end 14 to parabolical symmetry axis 18 in radial direction
Second distance H2 (that is, H1 < H2) on R.In other words, symmetry axis 18 is located closer at outer end 13, this makes connecting line " AB "
It is tilted relative to axial direction X to form the leading edge of sweepback.
In another embodiment shown in Fig. 3 B, first profile curve 121 can be alternatively formed so that from outer
The first distance H1 of end 13 to parabolical symmetry axis 18 is greater than from inner end 14 to the second distance H2 of parabolical symmetry axis 18
(that is, H1 > H2).In other words, symmetry axis 18 is located closer at inner end 14, this makes connecting line " AB " relative to axial direction X
It tilts to form the leading edge of sweepforward.
In another embodiment shown in Fig. 3 C, first profile curve 121 can also be formed so that from outer end 13
To parabolical symmetry axis 18 first distance H1 be equal to from inner end 14 to parabolical symmetry axis 18 second distance H2 (that is,
H1=H2).In this case, the middle on R between outer end 13 and inner end 14 in the axial direction of symmetry axis 18, this makes
Obtain the leading edge that connecting line " AB " forms straight (or not tilting) perpendicular to axial direction X.
It in some embodiments, can be based on the position for changing three design points to the more flexible adjustment of parabolic shape
The absolute value set executes.Fig. 4 A illustrates some key Design points of parabolic curve comprising two terminal As and B and
Vertex C.In this case, the axial position P of set point A, B and CxCombination, parabola can be uniquely determined out.This
Outside, in optimization process, pass through the boundary condition of some additional applications --- the axial position P on such as in the axial direction Xx's
Predefined scope, the span S on radial direction RRPredefined scope and vertex C predefined scope --- (such as just
For in terms of efficiency) parabola of optimization can be quickly determined out or select.
In addition, as it is known, parabola is mathematically equal to quadratic B é zier curve.Therefore, it can be based on and quadratic B
The design point of é zier curvilinear correlation connection optimizes contour curve.Fig. 4 B illustrates some key Designs of quadratic B é zier curve
Point comprising two terminal As and B and control point D.Control point D herein is defined such that connecting line " BD " and terminal B phase
It cuts, connecting line " AD " and terminal A are tangent.In this case, the axial position P of set point A, B and DxCombination, can be unique
Ground determines quadratic B é zier curve.Similarly, under some additional boundary conditions, (such as in terms of efficiency) optimization
Quadratic B é zier curve equally can be quickly determined out or select.
Fig. 5 schematically illustrates the diameter of the aerodynamics rectification part according to the embodiment of solution described herein
To sectional view.As shown, aerodynamics rectification part has the second contour curve including center line 19 in its section
122.Center line 19 is straight line and is aligned with axial direction X.In this case, which is configured to phase
For the symmetrical curve of axis 19 of axially X.For example, symmetrical curve can be formed to have the leading-edge radius of restriction
Circular curve.This symmetrical second contour curve 122 further improves the robustness of system.It will be appreciated, however, that with
The corresponding curved center line of asymmetrical contour curve 122 is also feasible.It is also to be understood that two side surfaces of connection
The second flat contour curve 122 be also it is possible.In other words, recess portion 15 described in the various embodiments about the disclosure is gone back
It can be applied to the aerodynamics rectification part with rectangular section observed on radial direction R.
In short, the various embodiments of the disclosure provide the aerodynamics rectification part of the optimization for exhaust diffuser.
Aerodynamics rectification part includes the leading edge of optimization, and leading edge has recess portion, this allows the air-flow with various outflow angles with low
Loss runs diffuser under various part-load conditions with the efficiency of raising by leading edge.Moreover, passing through optimization
The geometry of front edge area, the available further improvement of operation of the diffuser efficiency under various part-load conditions.
It should be appreciated that the above-mentioned specific embodiment of the disclosure is used for the purpose of illustrating or explaining the principle of the disclosure,
Rather than the limitation disclosure.Therefore, any modifications, equivalent replacements, and improvements etc. for not departing from the spirit and scope of the present invention should all
It is included within protection scope of the present invention.Meanwhile the appended claims of the disclosure are intended to cover and fall into claim
All changes and modification in range and boundary or in the equivalent of range and boundary.
Claims (10)
1. aerodynamics rectification part (1) of the one kind for a pillar of exhaust diffuser (10), the aerodynamics are whole
Stream portion (1) includes:
One leading edge portion (11), is exposed to the air-flow (30) reached from a upstream blade (2), and the aerodynamics is whole
Stream portion (1) the neighbouring blade (2) arrangement on an axial direction (X) of the exhaust diffuser (10),
It is characterized in that,
The leading edge portion (11) is on a radial direction (R) from an outer end of the aerodynamics rectification part (1)
(13) inner end (14) is extended to, wherein the leading edge portion is curved on the radial direction (R).
2. aerodynamics rectification part (1) according to claim 1, which is characterized in that
The curved leading edge portion includes the first profile curve (121) for being configured to a cubic Bézier curve, described
First profile curve (121) intersects with the outer end (13) and the inner end (14).
3. aerodynamics rectification part (1) according to claim 1, which is characterized in that
The curved leading edge portion includes being configured to a parabolical first profile curve (121), and the parabola has
The symmetry axis (18) extended on the axial direction (X), the first profile curve (121) with it is the outer end (13) and described
Inner end (14) intersection.
4. aerodynamics rectification part (1) according to claim 2 or 3, which is characterized in that
The first profile curve (121) is formed such that from the outer end (13) to the parabolical symmetry axis
(18) the first distance (H1) on the radial direction (R) is less than from the inner end (14) to described parabolical described right
Claim the second distance (H2) on the radial direction (R) of axis (18).
5. aerodynamics rectification part (1) according to claim 2 or 3, which is characterized in that
The first profile curve (121) is formed so that from the outer end (13) to the parabolical symmetry axis
(18) the first distance (H1) on the radial direction (R) is equal to from the inner end (14) to described parabolical described right
Claim the second distance (H2) on the radial direction (R) of axis (18).
6. aerodynamics rectification part (1) according to claim 2 or 3, which is characterized in that
The first profile curve (121) is formed so that from the outer end (13) to the parabolical symmetry axis
(18) the first distance (H1) on the radial direction (R) is greater than from the inner end (14) to described parabolical described right
Claim the second distance (H2) on the radial direction (R) of axis (18).
7. aerodynamics rectification part (1) according to claim 1, which is characterized in that
The aerodynamics rectification part has the center line (19) for including on the plane perpendicular to the radial direction (R)
Profile (122), wherein the center line (19) is straight line and is aligned with the axial direction (X).
8. a kind of exhaust diffuser (10), characterized by comprising:
Multiple aerodynamics rectification part (1) described in any one of -7 according to claim 1；And
One wheel hub (3), the wheel hub (3) are attached to described more at the inner end of the multiple aerodynamics rectification part (1)
A aerodynamics rectification part (1).
9. exhaust diffuser (10) according to claim 8, which is characterized in that
The multiple aerodynamics rectification part (1) is uniformly distributed on a circumferencial direction (C) of the wheel hub (3).
10. a kind of gas turbine, characterized by comprising:
The exhaust diffuser (10) according to any one of claim 8-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820683490.3U CN208518718U (en) | 2018-05-09 | 2018-05-09 | Aerodynamics rectification part, exhaust diffuser and the gas turbine of pillar for exhaust diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820683490.3U CN208518718U (en) | 2018-05-09 | 2018-05-09 | Aerodynamics rectification part, exhaust diffuser and the gas turbine of pillar for exhaust diffuser |
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| Publication Number | Publication Date |
|---|---|
| CN208518718U true CN208518718U (en) | 2019-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820683490.3U Active CN208518718U (en) | 2018-05-09 | 2018-05-09 | Aerodynamics rectification part, exhaust diffuser and the gas turbine of pillar for exhaust diffuser |
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| CN (1) | CN208518718U (en) |
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Effective date of registration: 20220909 Address after: Munich, Germany Patentee after: Siemens Energy International Address before: Munich Patentee before: SIEMENS AG |