US20140064951A1

US20140064951A1 - Root bow geometry for airfoil shaped vane

Info

Publication number: US20140064951A1
Application number: US13/603,634
Authority: US
Inventors: Renee J. Jurek; Thomas J. Praisner; Martin Hoeger
Original assignee: Individual
Current assignee: MTU Aero Engines AG; RTX Corp
Priority date: 2012-09-05
Filing date: 2012-09-05
Publication date: 2014-03-06
Also published as: WO2014074199A3; WO2014074199A2; EP2893143A4; EP2893143A2

Abstract

A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane.

Description

TECHNICAL FIELD

The present disclosure relates generally to airfoils for controlling a turning gas flow, and more particularly to a geometry for an airfoil shaped vane.

BACKGROUND OF THE INVENTION

Power generation systems that incorporate a compressor, a combustor, and a turbine arranged in a flow series from an inlet to an exhaust are typically referred to as gas turbine engines. The compressor compresses air from the inlet, the air is mixed with fuel in a combustor and ignited to produce combustion gasses that drive the turbine and are expelled at the exhaust. The gas turbine engine often includes a duct portion, connecting a high pressure turbine to a low pressure turbine. The duct portion includes a vane assembly with multiple airfoil shaped vanes that are arranged circumferentially about the duct and impart desirable flow characteristics onto the gas flowing through the duct. Similar vane assemblies and airfoil shaped vanes are used in other gas flow control applications.
In known configurations, the airfoil shaped vanes contact an interior end wall (referred to as an inner diameter wall) of the vane assembly at sharp, acute, angles on the pressure side of the vane. The sharpness of the junction between the vane and the inner diameter wall increases secondary flow losses within the system, thereby reducing the efficiency of the airfoil.

SUMMARY OF THE INVENTION

A stationary vane according to an exemplary embodiment of this disclosure, among other possible things includes a suction side surface and a pressure side surface. Each of the surfaces extends from a leading edge of the vane to a trailing edge of the vane. A chord line extends from a midpoint of the leading edge to a midpoint of the trailing edge. A radial line extends from a tip of the vane to an axis defined by vane assembly, and a bowing region at a root portion of the vane operable reduces secondary flow losses. The bowing region defines a junction angle between the suction side surface and an inner diameter mounting surface. The angle is greater than 70 degrees.
In a further embodiment of the foregoing stationary vane, the bowing region is a region of the root portion that diverges from the radial line.
In a further embodiment of any of the foregoing stationary vanes, the bowing region extends from approximately 5% span to 0% span of the vane.
In a further embodiment of any of the foregoing stationary vanes, the root portion diverges such that a 0% span of the root portion is the farthest diverged point of the root portion.
In a further embodiment of any of the foregoing stationary vanes, the vane abuts an inner diameter end wall in an installed configuration such that a junction between the vane and the end wall is approximately continuous.
In a further embodiment of any of the foregoing stationary vanes, the diverged root portion of the vane extends a full axial length of the chord line.
In a further embodiment of any of the foregoing stationary vanes, the diverged root portion of the vane extends from a throat point of said vane to a trailing edge of said vane.
In a further embodiment of any of the foregoing stationary vanes, further including a vane aspect ratio of less than or equal to 1.5.
In a further embodiment of any of the foregoing stationary vanes, the stationary vane is configured for use in a duct having a duct angle of at least 10 degrees.
A vane assembly for a gas flow duct according to an exemplary embodiment of this disclosure, among other possible things includes an inner diameter end wall defining an axis, an outer diameter end wall coaxial with the inner diameter end wall, a plurality of vanes arranged circumferentially between the inner diameter end wall and the outer diameter end wall. Each of said vanes further includes a suction side surface and a pressure side surface. Each of the surfaces extends from a leading edge of the vane to a trailing edge of the vane. A chord line extends from a midpoint of the leading edge to a midpoint of the trailing edge. A radial line extends from a tip of the vane to an axis defined by vane assembly, and a bowing region at a root portion of the vane operable reduces secondary flow losses. A junction angle between the suction side surface of the bowing region and the inner diameter endwall is greater than 70 degrees.
In a further embodiment of the foregoing vane assembly, the bowing region is a region of the root portion that diverges from the radial line.
In a further embodiment of any of the foregoing vane assemblies, the bowing region extends from approximately 5% span to 0% span of the vane.
In a further embodiment of any of the foregoing vane assemblies, the root portion diverges such that a 0% span of the root portion is the farthest diverged point of the root portion.
In a further embodiment of any of the foregoing vane assemblies, the vane abuts an inner diameter end wall in an installed configuration such that a junction between the vane and the end wall is approximately continuous.
In a further embodiment of any of the foregoing vane assemblies, the diverged root portion of the vane extends a full axial length of the chord line.
In a further embodiment of any of the foregoing vane assemblies, the diverged root portion of the vane extends from a throat point of the vane to a trailing edge of the vane.
In a further embodiment of any of the foregoing vane assemblies, each of the plurality of vanes has a vane aspect ratio of less than or equal to 1.5.
In a further embodiment of any of the foregoing vane assemblies, the inner diameter wall and the outer diameter wall define a duct having a duct angle of greater than 10 degrees.
In a further embodiment of any of the foregoing vane assemblies, the plurality of vanes is less than or equal to 20 vanes.
In a further embodiment of any of the foregoing vane assemblies, the plurality of vanes is a number of vanes selected from the set of 12, 18 and 20 vanes.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 schematically illustrates an example turbine engine.

FIG. 2 illustrates a highly schematic duct side view of a vane assembly.

FIG. 3 schematically illustrates a side view of a single airfoil shaped vane in a duct.

FIG. 4 a illustrates a sectional view of the isometric view of FIG. 3.

FIG. 4 b illustrates a top view of multiple vanes 410 in the vane assembly 100.

FIG. 5 illustrates a three dimensional view of the single airfoil of FIG. 4, in the context of a duct.

DETAILED DESCRIPTION

FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.
The engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.
The low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 and a low pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54. A combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54. duct 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46. The duct 57 further supports bearing systems 38 in the turbine section 28. The inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
The core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46. The duct 57 includes airfoils 59 which are in the core airflow path. The turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
FIG. 2 illustrates a highly schematic duct side view (meridional) of a vane assembly 100 for use in a duct, such as the duct 57. The vane assembly 100 defines a gas path 102 with an inner diameter wall 150 and an outer diameter wall 140, between which turbine gasses flow. The vane assembly 100 includes multiple vanes 110 arranged circumferentially about the vane assembly 100 in the gas path 102. In one example, the vane assembly includes less than twenty vanes. In alternate examples, there are twelve or eighteen vanes.
Each vane 110 has a leading edge 112 that contacts incoming gas flow and a trailing edge 114 where the gas flow finishes passing over the vane 110. The portion of the vane 110 contacting the outer diameter wall 140 is referred to as the vane tip 120, and the portion of the vane 110 contacting the inner diameter wall 150 is referred to as the vane root 130. Alternately, the portions are referred to as the tip portion 120 or the root portion 130, respectively. The vane assembly 100 defines an axis A about which the vane assembly 100 encircles. The axis A defined by the vane assembly 100 is collinear with the engine central longitudinal axis A. The duct defined by the inner diameter wall 150 and the outer diameter wall 114 has a duct angle 104 of greater than or equal to 10 degrees, where the duct angle 104 is defined by an angle between a midspan line of the vane 110 and the axis A.
The airfoil contouring of the vanes 110 causes a pressure differential in the gasses flowing through the vane assembly 100 over the vane 110. The pressure differential creates a high pressure side and a low pressure side on each vane 110 with the pressure on the high pressure side being greater than the pressure on the low pressure side. As a consequence of the pressure differential between the high pressure side and the low pressure side, gas flow exiting the vane assembly 100 is swirled and mixed. Each of the vanes 110 is joined to the inner diameter wall 150 at an inner junction and to the outer diameter wall 140 at an outer junction. The presence of the inner junction and the outer junction increases secondary flow losses on the gas passing through the vane assembly 100 due to the acute angle of the junctions on the pressure side of the junctions. The increased secondary flow losses lead to undesirable flow characteristics.
FIG. 3 illustrates a side view of a single vane 310 in the vane assembly 100 illustrated in FIG. 2. The vane 310 has a leading edge 312 and a trailing edge 314. The radial height of the vane from an inner diameter wall to an outer diameter wall is referred to as a vane span 320, with 0% span being at the root 316 of the vane 310, and 100% span being at the tip 318 of the vane 310. A vane chord line 330 is defined as a line connecting the midspan point of the leading edge 312 to the midspan point of the trailing edge 314. The axial chord length 332 is the length of the vane 310 from leading edge 312 to trailing edge 314 along the engine central longitudinal axis A. In a typical example, the root 316 portion of the vane 310 refers to the 0-5% span region of the vane 310, although it is understood that a larger range of spans could be incorporated into the root as well. Similarly, in a typical example the tip 318 portion of the vane 310 refers to the 95-100% span region of the vane 310. A radial line 340 is shown from a point on the tip 318 of the vane 310 and normal to the axis A. The radial stacking line and the axis A define a stacking plane. The illustrated vane has an aspect ratio of less than 1.5, with the aspect ratio being defined as: ((leading edge vane span length+trailing edge vane span length)/2)/(Axial chord length 332).
FIG. 4 a illustrates a sectional view of the vane assembly 100 illustrated in FIG. 2. FIG. 4 b illustrates a top view of multiple vanes 410 in the vane assembly 100. Each of the vanes 410 in the vane assembly 100 includes a root bowing feature 420 at the root portion of the vane 410. As can be seen in the top view of FIG. 4 b, each vane has a throat point 490 on the pressure side 430 of the vane 410. The throat point 490 is the point on the pressure side 430 of the vane 410 defining the smallest distance between the pressure side 430 of the vane 410 and the suction side 440 of the adjacent vane 410. The root bowing feature can be limited to an aft region of the root portion of the vane 410. In one example, the root bowing feature is located between the throat point 490 and the trailing edge of the vane 410. The root bowing feature 420 angles the root portion of the vane 410 toward a pressure side 430 of the vane and away from the suction side 440 of the vane.
The root bowing feature 420 can further be described as the root portion of the vane 410 deviating from the plane defined by the radial line 340 and the axis A as the vane approaches 0% span. The gradual deviation of the root portion from a radial line 340 in the illustrated bowing feature 420 increases the junction angle of the junction between the vane 410 and the inner diameter end wall 450 on the pressure side 430 of the vane 410. The angle of the root bowing feature 420 illustrated in the example of FIG. 4 is shown via the angle lines 470, 480 which are exaggerated for illustrative effect.
It is understood that the angle between the suction side 430 of the vane 410 and the inner diameter end wall 450 is related to, and causes, some of the secondary losses imparted on the gas flow passing through the vane assembly 100. By bowing the root portion of the vane 410 toward the pressure side of the vane 410, the angle defined by the junction between the root portion and the inner diameter end wall on the suction side is increased. Increasing the angle of the junction between the vane 410 and the inner diameter end wall 450 provides a more continuous transition between the vane 410 and the inner diameter end wall 450. The more continuous transition, in turn, reduces secondary flow losses. The junction angle is defined as the angle between a line 470 tangent to the end wall at the junction point and a line parallel to the vane 410 at the junction point.
In one example, the junction angle in a plane normal to axis A is 90 degrees (normal) relative to the tangent line 470 defined by the inner diameter end wall 450. It is understood, that in some practical implementations the suction side junction angle will be an acute angle (less than 90 degrees) and the pressure side junction angle will be an obtuse angle (greater than 90 degrees). In another example, the angle defined by the junction between the root portion and the inner diameter end wall is greater than seventy degrees, but remains an acute angle. In these practical implementations, the inclusion of the root bowing feature allows the suction side junction angle to be increased to as close to 90 degrees (normal) as possible. It is further understood that, absent additional features of the inner diameter end wall, increasing the suction side junction angle via the inclusion of a root bowing feature 420 will be accompanied by a decrease in the pressure side junction angle.
FIG. 5 provides a more detailed view of a single vane 510 and an inner diameter end wall 550 incorporating the above described root bow feature. As with the example of FIG. 5, the root bow feature 520 bows toward a pressure side 540 of the vane 510 and away from the suction side 530. The root bowing features 520 is defined as a section of the vane 510 that bows away from the plane defined by the stacking line (illustrated in FIG. 3) and the axis A, and toward the pressure side of the vane.
As can be appreciated by one of ordinary skill in the art having the benefit of this disclosure, the root bowing feature can be incorporated into replacement vanes for a vane assembly without requiring any alterations to the inner diameter, the outer diameter, or any other portion of the duct module. Alternately, a new vane assembly or new duct module incorporating vanes having the root bowing feature can be incorporated into an existing gas turbine engine without requiring retrofitting of other modules.
It can also be appreciated that the bowing feature can be incorporated at a tip portion of the vane and achieve similar benefits. The bowing feature can be incorporated at the tip portion either alone or in combination with the above described root bowing feature.
Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.

Claims

1. A stationary vane comprising:

a suction side surface and a pressure side surface, each of said surfaces extending from a leading edge of the vane to a trailing edge of the vane;

a chord line extending from a midpoint of the leading edge to a midpoint of the trailing edge;

a radial line extending from a tip of the vane to an axis defined by vane assembly; and

a bowing region at a root portion of said vane operable reduce secondary flow losses, wherein the bowing region defines a junction angle between the suction side surface and an inner diameter mounting surface, wherein the angle is greater than 70 degrees.

2. The stationary vane of claim 1, wherein said bowing region is a region of said root portion that diverges from said radial line.

3. The stationary vane of claim 2, wherein said bowing region extends from approximately 5% span to 0% span of the vane.

4. The stationary vane of claim 2, wherein said root portion diverges such that a 0% span of the root portion is the farthest diverged point of the root portion.

5. The stationary vane of claim 1, wherein said vane abuts an inner diameter end wall in an installed configuration such that a junction between the vane and the end wall is approximately continuous.

6. The stationary vane of claim 1, wherein the diverged root portion of the vane extends a full axial length of the chord line.

7. The stationary vane of claim 1, wherein the diverged root portion of the vane extends from a throat point of said vane to a trailing edge of said vane.

8. The stationary vane of claim 1, further comprising a vane aspect ratio of less than or equal to 1.5.

9. The stationary vane of claim 1, wherein the stationary vane is configured for use in a duct having a duct angle of at least 10 degrees.

10. A vane assembly for a gas flow duct comprising:

an inner diameter end wall defining an axis;

an outer diameter end wall coaxial with said inner diameter end wall;

a plurality of vanes arranged circumferentially between said inner diameter end wall and said outer diameter end wall, wherein each of said vanes further comprises:

a bowing region at a root portion of said vane operable reduce secondary flow losses, wherein a junction angle between the suction side surface of the bowing region and the inner diameter endwall is greater than 70 degrees.

11. The vane assembly of claim 10, wherein said bowing region is a region of said root portion that diverges from said radial line.

12. The vane assembly of claim 11, wherein said bowing region extends from approximately 5% span to 0% span of the vane.

13. The vane assembly of claim 11, wherein said root portion diverges such that a 0% span of the root portion is the farthest diverged point of the root portion.

14. The vane assembly of claim 10, wherein said vane abuts an inner diameter end wall in an installed configuration such that a junction between the vane and the end wall is approximately continuous.

15. The vane assembly of claim 10, wherein the diverged root portion of the vane extends a full axial length of the chord line.

16. The stationary vane of claim 1, wherein the diverged root portion of the vane extends from a throat point of said vane to a trailing edge of said vane.

17. The vane assembly of claim 10, wherein each of said plurality of vanes has a vane aspect ratio of less than or equal to 1.5.

18. The vane assembly of claim 10, wherein said inner diameter wall and said outer diameter wall define a duct having a duct angle of greater than 10 degrees.

19. The vane assembly of claim 10, wherein said plurality of vanes is less than or equal to 20 vanes.

20. The vane assembly of claim 19, wherein said plurality of vanes is a number of vanes selected from the set of 12, 18 and 20 vanes.