CN105443162B - Engine transition section and aero-engine - Google Patents
Engine transition section and aero-engine Download PDFInfo
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- CN105443162B CN105443162B CN201410499761.6A CN201410499761A CN105443162B CN 105443162 B CN105443162 B CN 105443162B CN 201410499761 A CN201410499761 A CN 201410499761A CN 105443162 B CN105443162 B CN 105443162B
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Abstract
The invention discloses an engine transition section and an aero-engine, and relates to the technical field of aero-engines. The technical problem that the aerodynamic performance of a transition section in the prior art is poor is solved. The engine transition section comprises an outer end wall, an inner end wall and a supporting plate arranged between the outer end wall and the inner end wall; the supporting plate is provided with an air flow passage penetrating through the supporting plate; air flow flowing through a pressure surface of the supporting plate passes through the air flow passage towards a suction surface of the supporting plate and drives low-energy fluid around the suction surface to flow towards the lower stream. The aero-engine comprises the engine transition section provided by the technical scheme, the outer end wall is the inner surface of a peripheral machine case, and the inner end wall is the outer surface of a hub. According to the invention, the aerodynamic performance of the transition section is improved.
Description
Technical field
The present invention relates to aero-engine technology field, more particularly to a kind of engine transition section and the electromotor is set
The aero-engine of changeover portion.
Background technology
Casing is also called " changeover portion " (English can be translated between stage of turbine:TRANSITION DUCT), it is located at high pressure whirlpool
Between wheel, low-pressure turbine, guide functions are played, be one of critical component of aero-engine.Connect on changeover portion high-pressure turbine outlet,
Its outlet connection low-pressure turbine entrance (or claim:Low-pressure turbine import), therefore, the aeroperformance of changeover portion affects low pressure strongly
The aeroperformance of turbine.Changeover portion by support plate, upper end wall (or claim:Outer end wall) and lower end wall (or claim:Inner end wall) constitute, its
The key of pneumatic design is exactly the Design and optimization to wheel hub (i.e. inner end wall), casing (i.e. outer end wall) and support plate molded line.Typically
Ground, when the exit flow of upstream high turbine flows into changeover portion, the load-carrying construction inside changeover portion can adopt outsourcing support plate pair
Flowing through the air-flow of changeover portion carries out water conservancy diversion.
Applicants have discovered that:At least there is following technical problem in prior art:
In due to prior art, when the load-carrying construction of transition intrasegmental part is entered using the convection current of outsourcing support plate through the air-flow for crossing section
During row water conservancy diversion, easily in support plate trailing edge, (English can be translated into the air-flow of inflow changeover portion:TRAILNG EDGE) nearby produce
It is estranged from this separation can affect the aerodynamic characteristic of changeover portion itself, reduce the total pressure recovery performance of changeover portion, improve changeover portion
The pressure loss, with the development of separation bubble can directly affect changeover portion outlet flow quality, also have impact on down stream low pressure
The aeroperformance of turbine inlet.
The content of the invention
One of purpose of the present invention is the boat for proposing a kind of engine transition section and arranging the engine transition section
Empty electromotor, solves the poor technical problem of aeroperformance that prior art has changeover portion.Many skills that the present invention is provided
Many technique effects elaboration as detailed below that optimal technical scheme in art scheme can be generated.
For achieving the above object, the invention provides technical scheme below:
Engine transition section provided in an embodiment of the present invention, including outer end wall, inner end wall and it is arranged on the outer end wall
With the support plate between the inner end wall, wherein:
The gas channel of the support plate is provided through on the support plate, from the air-flow energy that the pressure face of the support plate flows through
The suction surface of the support plate is flowed to through the gas channel and drive the low energy fluid around the suction surface to flow to downstream.
Preferably or alternatively, in embodiment, the gas channel is formed for air-flow gap, and the air-flow gap will be described
Support plate is divided into front supporting plate and rear carrier plate.
Preferably or alternatively in embodiment, the front supporting plate and the rear carrier plate are each blade-shaped, it is described before
Into main wing, the rear carrier plate forms wing flap to plate shape, and the gas channel is arranged on the trailing edge of the support plate.
Preferably or alternatively, in embodiment, the chord length of the wing flap is the 5%~45% of the chord length of the support plate.
Preferably or alternatively, in embodiment, the chord length of the wing flap is the 10%~30% of the chord length of the support plate.
It is identical with slope on the pressure face of the main wing on the pressure face of the wing flap preferably or alternatively in embodiment
Point and the leading edge point of the wing flap between minimum range be length of the wing flap on the electromotor axial direction
25%~35%.
Preferably or alternatively, in embodiment, the trailing edge of the main wing is provided with water conservancy diversion plane, and the water conservancy diversion plane is formed
One of side wall in two relative side walls of the air-flow gap position.
Preferably or alternatively in embodiment, the water conservancy diversion plane and the junction of the pressure face of the main wing and described
Water conservancy diversion plane is provided with fillet or chamfering with the junction of the suction surface of the main wing.
Preferably or alternatively in embodiment, with slope identical on the trailing edge surface of the main wing in the flap surface
The outer contour on the surface between point and the leading edge point of the wing flap is curve, and the curve meets elliptic equation or parabola side
Journey:The elliptic equation is y2+ ax2+bxy+cx=0, wherein:X is the abscissa value of each point on curve, and y is each point on curve
Ordinate value, a, b, c be from setting coefficient.
Preferably or alternatively, in embodiment, a, the b, the respective values of the c are -5~5.
Preferably or alternatively, in embodiment, the gas channel is air-flow through hole.
Preferably or alternatively, in embodiment, the air-flow through hole is arranged on portion of the support plate be close to the outer end wall
Point, be arranged on the support plate be close to the part of the inner end wall or be arranged on the support plate along the electromotor in the radial direction
Medium position.
Aero-engine provided in an embodiment of the present invention, including the engine transition that arbitrary technical scheme of the invention is provided
Section, the outer end wall is the inner surface of periphery casing, and the inner end wall is the outer surface of wheel hub.
Preferably or alternatively, in embodiment, the gas channel is formed for air-flow gap, and the air-flow gap will be described
Support plate is divided into front supporting plate and rear carrier plate, and the aero-engine also includes cooling gas input equipment, and the cooling gas are defeated
Enter the cooling gas delivery outlet of device towards the gas channel be close to the outer end wall or the position of the inner end wall.
Based on above-mentioned technical proposal, the embodiment of the present invention can at least produce following technique effect:
Due to arranging (preferably at the trailing edge of support plate) on the support plate in engine transition section provided in an embodiment of the present invention
Have the gas channel through support plate, when upstream airflow (for example:High-pressure turbine exit flow) when flowing into changeover portion, due to air-flow it is logical
The presence in road (gap preferably between wing flap and main wing is formed), the air-flow of pressure face can flow to suction through gas channel
Face,
Because the fluid for flowing to suction surface has larger kinetic energy, under it can drive the low energy fluid of suction surface to flow to
Trip, it is to avoid flow separation occurs at the trailing edge of support plate, so improving the aeroperformance of changeover portion, prior art is solved
There is the poor technical problem of the aeroperformance of changeover portion.
Description of the drawings
Accompanying drawing described herein is used for providing a further understanding of the present invention, constitutes the part of the application, this
Bright schematic description and description does not constitute inappropriate limitation of the present invention for explaining the present invention.In the accompanying drawings:
Fig. 1 is the schematic diagram of the support plate outer surface air-flow streamline of engine transition section in prior art;
The schematic diagram of the blade profile of the support plate of the engine transition section that Fig. 2 is provided by the embodiment of the present invention;
The schematic diagram of the support plate outer surface air-flow streamline of the engine transition section that Fig. 3 is provided by the embodiment of the present invention;
The enlarged diagram of the blade profile of the wing flap of the support plate of the engine transition section that Fig. 4 is provided by the embodiment of the present invention;
The enlarged diagram of the blade profile of the support plate of the engine transition section that Fig. 5 is provided by the embodiment of the present invention;
Fig. 6 is the enlarged diagram of the blade profile of wing flap shown in Fig. 5;
Reference:1st, support plate;11st, main wing;12nd, wing flap;13rd, gas channel;121st, water conservancy diversion plane;14th, fillet, E,
Point;F, point;G, point;H, point;I, point;J, point;K, point;L, point;M, point.
Specific embodiment
Be referred to accompanying drawing Fig. 1~Fig. 6 below and word content understand present disclosure and the present invention with it is existing
Distinctive points between technology.Hereafter accompanying drawing and enumerate the present invention some alternative embodiments by way of, to the present invention
Technical scheme (including optimal technical scheme) is described in further detail.It should be noted that:Any skill in the present embodiment
Art feature, any technical scheme are one or more in the technical characteristic or optional technical scheme of plurality of optional, in order to
Description is succinct need in presents cannot the exhaustive present invention all alternative technical characteristic and alternative technical side
Case, the embodiment for being also not easy to each technical characteristic emphasizes that it is one of optional numerous embodiments, so this area
Technical staff should know:Any two for arbitrary technological means that the present invention is provided being replaced or providing the present invention
Individual or more technological means or technical characteristic are combined mutually and obtain new technical scheme.Any skill in the present embodiment
Art feature and any technical scheme are not limited the scope of the invention, and protection scope of the present invention should include this area
Technical staff does not pay the thinkable any alternate embodiments of creative work institute and those skilled in the art by the present invention
Any two of offer or more technological means or technical characteristic technical scheme new obtained from being combined mutually.
Embodiments providing one kind can improve, suppress flow separation, the ideal electromotor of aeroperformance
Changeover portion and the aero-engine of the engine transition section is set.
The technical scheme that the present invention is provided is illustrated in more detail with reference to Fig. 2~Fig. 6.
As shown in Fig. 2~Fig. 6, the engine transition section that the embodiment of the present invention is provided, including outer end wall, inner end wall and
The support plate as shown in Figure 21 being arranged between outer end wall and inner end wall, wherein:
The gas channel 13 of support plate 1 is provided through (preferably at the trailing edge of support plate 1) on support plate 1, from the pressure of support plate 1
Under the air-flow that surface current is crossed can flow to the suction surface of support plate 1 and drives low energy fluid around suction surface to flow to through gas channel 13
Trip.
Due to arranging (preferably at the trailing edge of support plate 1) on support plate 1 in engine transition section provided in an embodiment of the present invention
Have the gas channel 13 through support plate 1, when upstream airflow (for example:High-pressure turbine exit flow) flow into changeover portion when, due to gas
The presence of circulation road 13 (gap preferably between wing flap 12 and main wing 11 is formed), the air-flow of pressure face can be through gas channel
13 flow to suction surface, and the fluid for flowing to suction surface has larger kinetic energy, and it can drive the low energy fluid stream of suction surface
Downstream, it is to avoid flow separation occurs at the trailing edge of support plate 1, so improve the aeroperformance of changeover portion.
Used as preferably or alternatively embodiment, gas channel 13 is formed for air-flow gap, and air-flow gap separates support plate 1
For front supporting plate and rear carrier plate.Not only bore is larger in air-flow gap, and the aerodynamic loss that the air-flow to passing through is caused is less, and is easy to
Arrange, the material of the consuming of support plate 1 can be saved.
Used as preferably or alternatively embodiment, front supporting plate and rear carrier plate are each blade-shaped, and front supporting plate forms main wing
11, rear carrier plate forms wing flap 12.Gas channel 13 is arranged on the trailing edge of support plate 1.Blade-shaped structure is caused to the air-flow for passing through
Aerodynamic loss is less, and preferable to the guide effect of air-flow.
Used as preferably or alternatively embodiment, the chord length of wing flap 12 is the 5%~45% of the chord length of support plate 1, wing flap 12
Chord length be preferably support plate 1 chord length 10%~30%.Above-mentioned size value may insure the position for head piece of gas channel 13
Put the surrounding flow of close support plate 1 and the more serious region of flow separation occurs, it is possible thereby to more effectively suppress flow separation
The harm for causing.
As preferably or alternatively embodiment, the pressure face (side of the flow inlet of close gas channel 13 of wing flap 12
Surface) on leading edge point with slope identical point on the pressure face (the preferably trailing edge surface of main wing 11) of main wing 11 and wing flap 12
Between minimum range for length of the wing flap 12 on electromotor axial direction 25%~35%.Above-mentioned size value may insure
The width dimensions of gas channel 13 are ideal, and then guarantee the less situation of the flow losses that gas channel 13 is caused to air-flow
Under, the harm for effectively suppressing flow separation to cause.
Used as preferably or alternatively embodiment, the trailing edge of main wing 11 is provided with water conservancy diversion plane 121, the shape of water conservancy diversion plane 121
One of side wall in two relative side walls of air-flow gap position.
Water conservancy diversion plane 121 is easy to manufacture, is processed, and the aerodynamic loss that the air-flow to flowing through is caused is less.
As preferably or alternatively embodiment, junction and water conservancy diversion of the water conservancy diversion plane 121 with the pressure face of main wing 11
Plane 121 is provided with fillet 14 or chamfering, preferably fillet 14 with the junction of suction surface.
Fillet 14 or chamfering not only can avoid stress concentration at the trailing edge arris of main wing 11, and intensity is higher, but also
Its loss to causing through air-flow can be reduced.
As preferably or alternatively embodiment, with slope identical point on the trailing edge surface of main wing 11 on the surface of wing flap 12
And the outer contour on the surface between the leading edge point of wing flap 12 is curve, curve meets elliptic equation or parabolic equation:It is oval
Equation is y2+ax2+ bxy+cx=0, wherein:X be curve on each point abscissa value, y be curve on each point ordinate value, a,
B, c are from setting coefficient.The value of a, b, c can be -5~5, naturally it is also possible to for other numerical value.By changing taking for a, b, c
Value can change bent curvature of a curve, and then change the shape on the surface of wing flap 12.
Above-mentioned shape can be reduced as far as the aerodynamic loss that air-flow of the surface of wing flap 12 to flowing through is caused.
As shown in Figure 5 and Figure 6, the chord length of wing flap 12 can be the 10%~30% of the chord length of support plate 1 in the present invention.Wing flap 12
Specific design method include the method for designing one of wing flap 12 and the method for designing two of wing flap 12, it is specific as follows:
The method for designing one of wing flap 12:
Wing flap 12 be made up of a plurality of line segment including:
Line segment one:Point L is to trailing edge section;Distances of the point L away from the trailing edge point M of wing flap 12 accounts for wing flap 12 on electromotor axial direction
The 30%~40% of length.Point L is identical with the slope of point A on main wing 11.
The streamline of main wing 11 can be determined by NACA series blade profile data, the streamline coordinate of main wing 11 is, it is known that can try to achieve at point A, C
Coordinate, by point A, point C (C is as close as possible for point A, point) line segment AC is determined, is extended line segment AC by point L and is extended, and can be obtained
Line segment CAL and its extended line.
Line segment two:Point E is to leading edge segments;Distances of the point E away from leading edge point H of wing flap 12 accounts for wing flap 12 on electromotor axial direction
The 25%~35% of length;With line segment one in the same manner, obtain the line segment DBE that is made up of point B, point D (B, D are as close as possible for point) and its
Extended line, it is considered to which processing technique etc. is required to determine trailing edge diameter (such as 4mm), obtained while be inscribed within the circle of line segment BE, AL, then
The position Crestor of the trailing edge point of wing flap 12.
Curve three:To point L, the part line segment is at least made up of point E to point H two parts:Curve EH, curve HL, its midpoint H
For the leading edge point of wing flap 12.To improve curve precision, the curve can artificially increase line segment number.This case only as a example by two sections, curve
The separately available elliptic equation of EH, curve HL is realized:y2+ax2+ bxy+cx=0) (a, b, c are the coefficient that can be set certainly in formula, by
The controllable curve EH of these coefficients, the amount of curvature of curve HL;In addition to elliptic equation, parabolic equation be also capable of achieving curve EH,
The configuration design of curve HL), this equation meets the infinitely-great condition of head slope automatically.Such as:Curve EH can choose ellipse side
Journey:Curve HL can choose elliptic equation:
The method for designing two of wing flap 12:
Blade shape construction software is used, according to flow field streamline details, by adjusting the molded line of wing flap 12, Flow Field Calculation is carried out and is divided
Analysis, iteration carries out above-mentioned steps up to flow field without being clearly separated, in the case of flow field is without separation, it is determined that meeting the wing flap 12 of condition
Profile.
The specific design of the trailing edge of main wing 11 has following two methods in the embodiment of the present invention:
The trailing edge method for designing one of main wing 11:The trailing edge of main wing 11 also can be by realizing using elliptic equation.
The trailing edge method for designing two of main wing 11:By be directly connected to the afterbody top airfoil of main wing 11, two end points A of lower aerofoil,
Point B, then two interior angle roundings upper and lower to aerofoil realization.
Embodiment 2:
The present embodiment is substantially the same manner as Example 1, and its difference is:Gas channel 13 is air-flow through hole in the present embodiment.
The support plate 1 of setting air-flow through hole has to be easy to process, manufactures, transports, and the higher advantage of structural strength.
Used as preferably or alternatively embodiment, air-flow through hole is arranged on the part of the close outer end wall of support plate 1, is arranged on
The part of the close inner end wall of plate 1 is arranged on the medium position along electromotor in the radial direction of support plate 1.Arrangement above position is equal
Can be different degrees of play a part of suppress the surrounding flow separation of support plate 1.Certainly, gas channel 13 can also be air-flow through hole
With the combination in air-flow gap, for example:The part of gas channel 13 is air-flow through hole, is partly air-flow gap.
As shown in Fig. 2~Fig. 6, aero-engine provided in an embodiment of the present invention, including arbitrary technical scheme of the invention carries
For engine transition section, outer end wall for periphery casing inner surface, inner end wall for wheel hub outer surface.Aero-engine is suitable
Adopt the engine transition section that arbitrary technical scheme of the invention is provided to improve the harm that it suppresses flow separation to produce, improve it
Aeroperformance.
Used as preferably or alternatively embodiment, gas channel 13 is formed for air-flow gap, and air-flow gap separates support plate 1
For front supporting plate and rear carrier plate, aero-engine also includes that cooling gas input equipment (or claims:Air intake installation), cooling gas input
The cooling gas delivery outlet of device is towards the close outer end wall of gas channel 13 or the position of inner end wall.Air intake installation can be improved
The cooling effect of section is crossed, and then extends service life and the safety of transition section structure.
The technical scheme that the embodiment of the present invention 1 is provided is contrasted with prior art experimental data:
Changeover portion | Total pressure recovery coefficient % | Total pressure loss coefficient % |
Prior art | 99.326 | 8.273 |
The present invention | 99.426 | 6.974 |
Improvement amplitude | +0.1 | -1.299 |
Arbitrary technical scheme disclosed in the invention described above unless otherwise stated, if it discloses numerical range, then
Disclosed numerical range is preferred numerical range, it is any it should be appreciated by those skilled in the art:Preferred numerical range
The only obvious or representative numerical value of technique effect in many enforceable numerical value.Due to numerical value it is more, it is impossible to
Exhaustion, so just open component values of the invention are to illustrate technical scheme, also, the above-mentioned numerical value enumerated is not
The restriction to the invention protection domain should be constituted.
If the words such as " first ", " second " are used herein to limit parts, those skilled in the art should
This knows:" first ", the use of " second " are intended merely to facilitate in description to be distinguished as without Stated otherwise to parts
Outward, above-mentioned word does not have special implication.
Meanwhile, if the invention described above discloses or relate to the parts or structural member of connection fastened to each other, then, except another
There is statement outer, be fixedly connected and can be understood as:Can releasably be fixedly connected (such as using bolt or mode connects for screw), it is also possible to
It is interpreted as:Non-removable to be fixedly connected (such as riveting, welding), certainly, connection fastened to each other can also be integral type structure
(for example manufacturing using casting technique is integrally formed) replaces (substantially cannot be using except integrally formed technique).
In addition, the art for representing position relationship or shape applied in arbitrary technical scheme disclosed in the invention described above
Unless otherwise stated its implication includes approximate with its, similar or close state or shape to language.The either component that the present invention is provided
Both can be to be assembled by multiple single ingredients, it is also possible to the separate part that the technique that is one of the forming is manufactured.
Finally it should be noted that:Above example is only to illustrate technical scheme rather than a limitation;To the greatest extent
Pipe has been described in detail with reference to preferred embodiment to the present invention, and those of ordinary skill in the art should be understood:Still
The specific embodiment of the present invention can be modified or equivalent is carried out to some technical characteristics;Without deviating from this
The spirit of bright technical scheme, it all should cover in the middle of the technical scheme scope being claimed in the present invention.
Claims (10)
1. a kind of engine transition section, it is characterised in that including outer end wall, inner end wall and be arranged on the outer end wall with it is described
Support plate between inner end wall, wherein:
The gas channel of the support plate is provided through on the support plate, the air-flow flow through from the pressure face of the support plate can be passed through
The gas channel flows to the suction surface of the support plate and drives the low energy fluid around the suction surface to flow to downstream, the gas
Circulation road is formed for air-flow gap, and the support plate is divided into front supporting plate and rear carrier plate by the air-flow gap, the front supporting plate and
The rear carrier plate is each blade-shaped, and the front supporting plate forms main wing, and the rear carrier plate forms wing flap, and the gas channel sets
Put the trailing edge in the support plate.
2. engine transition section according to claim 1, it is characterised in that the chord length of the wing flap is the string of the support plate
Long 5%~45%.
3. engine transition section according to claim 1, it is characterised in that the chord length of the wing flap is the string of the support plate
Long 10%~30%.
4. engine transition section according to claim 1, it is characterised in that with the main wing on the pressure face of the wing flap
Pressure face on minimum range between slope identical point and the leading edge point of the wing flap be the wing flap in the electromotor
25%~35% of length on axial direction.
5. engine transition section according to claim 1, it is characterised in that the trailing edge of the main wing is provided with water conservancy diversion and puts down
Face, the water conservancy diversion plane forms the one of side wall in two relative side walls of the air-flow gap position.
6. engine transition section according to claim 5, it is characterised in that the pressure of the water conservancy diversion plane and the main wing
The junction in face and the water conservancy diversion plane are provided with fillet or chamfering with the junction of the suction surface of the main wing.
7. engine transition section according to claim 1, it is characterised in that with the tail of the main wing in the flap surface
The outer contour on the surface on edge surface between slope identical point and the leading edge point of the wing flap is curve, and the curve meets
Elliptic equation or parabolic equation:The elliptic equation is y2+ax2+ bxy+cx=0, wherein:X is the abscissa of each point on curve
Value, y is the ordinate value of each point on curve, and a, b, c are from setting coefficient.
8. engine transition section according to claim 7, it is characterised in that a, the b, the respective values of the c
It is -5~5.
9. a kind of aero-engine, it is characterised in that described outer including the arbitrary described engine transition section of claim 1-8
End wall is the inner surface of periphery casing, and the inner end wall is the outer surface of wheel hub.
10. aero-engine according to claim 9, it is characterised in that the gas channel is formed for air-flow gap, institute
State air-flow gap and the support plate is divided into into front supporting plate and rear carrier plate, the aero-engine also includes cooling gas input dress
Put, the cooling gas delivery outlet of the cooling gas input equipment towards the gas channel be close to the outer end wall or it is described in
The position of end wall.
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CN202202902U (en) * | 2011-06-30 | 2012-04-25 | 中航商用航空发动机有限责任公司 | Intermediate case for aeroengine |
CN203515810U (en) * | 2013-09-09 | 2014-04-02 | 中国科学院工程热物理研究所 | Transition section structure of high-low-pressure turbine |
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US6715983B2 (en) * | 2001-09-27 | 2004-04-06 | General Electric Company | Method and apparatus for reducing distortion losses induced to gas turbine engine airflow |
ES2746966T3 (en) * | 2012-06-01 | 2020-03-09 | MTU Aero Engines AG | Transition channel for a turbomachine and turbomachine |
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US2914241A (en) * | 1955-11-30 | 1959-11-24 | Gen Electric | Means for adjusting the flow characteristics of fluid flow machines |
EP1112928A2 (en) * | 1999-12-31 | 2001-07-04 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Airfoil with performance enhancing trailing edge |
CN1955441A (en) * | 2005-10-25 | 2007-05-02 | 联合工艺公司 | Variable geometry inlet guide vane |
EP1947294A2 (en) * | 2007-01-17 | 2008-07-23 | United Technologies Corporation | Airfoil with device against boundary layer separation |
CN101779003A (en) * | 2008-01-21 | 2010-07-14 | 三菱重工业株式会社 | Turbine blade-cascade end wall |
CN202202902U (en) * | 2011-06-30 | 2012-04-25 | 中航商用航空发动机有限责任公司 | Intermediate case for aeroengine |
CN203515810U (en) * | 2013-09-09 | 2014-04-02 | 中国科学院工程热物理研究所 | Transition section structure of high-low-pressure turbine |
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