WO2014007994A1

WO2014007994A1 - Airfoil for improved flow distribution with high radial offset

Info

Publication number: WO2014007994A1
Application number: PCT/US2013/046766
Authority: WO
Inventors: Thomas J. Praisner; Noel Modesto-Madera
Original assignee: United Technologies Corp
Current assignee: RTX Corp
Priority date: 2012-07-02
Filing date: 2013-06-20
Publication date: 2014-01-09
Anticipated expiration: 2015-01-02
Also published as: EP2867510A4; EP2867510B1; US20140003925A1; US9157326B2; EP2867510A1

Description

AIRFOIL FOR IMPROVED FLOW DISTRIBUTION WITH HIGH RADIAL

OFFSET

TECHNICAL FIELD

[0001] The present disclosure is directed to stationary vane assemblies for airflow ducts, and more particularly to a spanwise throat angle distribution for the same.

BACKGROUND OF THE INVENTION

[0002] Mechanical systems incorporating airflow ducts, such as jet engines, often include stationary vanes within the airflow ducts. The stationary vanes control airflow through the duct and impart desirable flow characteristics, such as turning, onto the airflow. Known stationary (stator) vanes with a low aspect ratio are typically included in ducts having a relatively long exit duct portion after the trailing edge of the vane. As a result of the low aspect ratio and the relatively long exit duct portion, flow quality problems can arise at the inner diameter and the outer diameter of the duct.

SUMMARY OF THE INVENTION

[0003] A vane assembly for a duct according to an exemplary embodiment of this disclosure, among other possible things includes a plurality of vanes arranged circumferentially about an axis defined by a duct, each of said plurality of vanes has a throat distance defining a shortest distance between the vane and an adjacent vane at a constant span, the throat distance defines a throat angle relative to a line tangential to a trailing edge of each of said plurality of vanes, and the throat angle of each vane at mid-span is greater than the throat angle at the tip region of each vane.

[0004] In a further embodiment of the foregoing vane assembly, the stationary duct has a duct angle of at least ten degrees, relative to the axis defined by the stationary duct.

[0005] In a further embodiment of any of the foregoing vane assemblies, each vane in said plurality of vanes has an aspect ratio of less than or equal to 1.5.

[0006] In a further embodiment of any of the foregoing vane assemblies, the plurality of vanes includes an even number of vanes.

[0007] In a further embodiment of any of the foregoing vane assemblies, the plurality of vanes includes less than or equal to twenty vanes. [0008] In a further embodiment of any of the foregoing vane assemblies, further including a root throat angle at a root region of the vane, wherein the root throat angle is less than the throat angle.

[0009] In a further embodiment of any of the foregoing vane assemblies, the root throat angle is a throat angle measured at less than or equal to 5% span of the vane.

[0010] In a further embodiment of any of the foregoing vane assemblies, the tip region throat angle is a throat angle measured at greater than or equal to 95% span of the vane.

[0011] In a further embodiment of any of the foregoing vane assemblies, the mid-span throat angle is a smallest throat angle in a range of throat angles between 5% span and 95 % span.

[0012] In a further embodiment of any of the foregoing vane assemblies, the mid-span throat angle is a smallest throat angle in a range of throat angles between 45% span and 55% span.

[0013] In a further embodiment of any of the foregoing vane assemblies, an airflow at an outer diameter of said vane assembly is elevated relative to an airflow at a mid- span region of the vane assembly.

[0014] In a further embodiment of any of the foregoing vane assemblies, an airflow at an inner diameter of said vane assembly is elevated relative to an airflow at a mid- span region of the vane assembly.

[0015] A jet engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas path duct having a vane assembly. The vane assembly has a plurality of vanes arranged circumferentially about an axis defined by the gas path duct. Each of said plurality of vanes has a throat distance defining a shortest distance between the vane and an adjacent vane at a constant span. The throat distance defines a throat angle relative to a line tangential to a trailing edge of each of said plurality of vanes. The throat angle of each vane at mid-span is greater than the throat angle at the tip region of each vane.

[0016] In a further embodiment of the foregoing jet engine, the gas path duct has a duct angle of at least ten degrees, relative to the axis defined by the gas path duct.

[0017] In a further embodiment of any of the foregoing jet engines, each of said plurality of vanes has an aspect ratio of less than or equal to 1.5.

[0018] In a further embodiment of any of the foregoing jet engines, the plurality of vanes is an even number of vanes. [0019] In a further embodiment of any of the foregoing jet engines, the plurality of vanes is less than or equal to twenty vanes.

[0020] In a further embodiment of any of the foregoing jet engines, the plurality of vanes further define a root throat angle, wherein the root throat angle is less than the mid-span throat angle.

[0021] In a further embodiment of any of the foregoing jet engines, the root throat angle is a throat angle measured at less than or equal to 5% span of the vane.

[0022] In a further embodiment of any of the foregoing jet engines, the tip region throat angle is a throat angle measured at greater than or equal to 95% span of the vane.

[0023] In a further embodiment of any of the foregoing jet engines, the mid- span throat angle is a smallest throat angle in a range of throat angles between 5% span and 95 % span.

[0024] In a further embodiment of any of the foregoing jet engines, the mid- span throat angle is a smallest throat angle in a range of throat angles between 45% span and 55% span.

[0025] In a further embodiment of any of the foregoing jet engines, an airflow at an outer diameter of said vane assembly is elevated relative to an airflow at a mid-span region of the vane assembly.

[0026] In a further embodiment of any of the foregoing jet engines, an airflow at an inner diameter of said vane assembly is elevated relative to an airflow at the mid-span region of the vane assembly.

[0027] 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

[0028] Figure 1 illustrates a side view of a single stationary vane of a vane assembly in an airflow duct.

[0029] Figure 2 illustrates a top (tip) view of two stationary vanes in the stationary vane assembly of Figure 1.

[0030] Figure 3a illustrates an outer diameter layer of a vane in one example vane assembly arrangement.

[0031] Figure 3b illustrates a top view of a mid-span layer of the example vane assembly arrangement of Figure 3a. [0032] Figure 4 illustrates a top view of a root layer of an optional feature of the example vane assembly arrangement of Figure 3a.

[0033] Figure 5 illustrates a chart showing a progression of throat angles related to percent span of the example arrangement of Figures 3a, 3b and 4.

DETAILED DESCRIPTION

[0034] Figure 1 illustrates a stationary vane assembly 10 in a duct 20. The duct 20 is a circular duct and defines an axis A running through the center of the duct 20. The vane assembly 10 includes multiple individual vanes 12 arranged circumferentially about the axis A. In one example, the vanes 12 are substantially identical, and are equidistantly spaced about the vane assembly 10. In one example, there are less than or equal to 20 vanes. In an alternate example there is an even number of vanes. The duct 20 has a duct angle 70 defined as the angle of a mid-span line 72 of the vane 12 relative to the axis A defined by the duct 20. The mid-span line 72 is drawn along the vane 12 at 50% span. An airflow 30 through the duct 20 is shown including arrows illustrating the direction of the airflow 30. The airflow 30 encounters a leading edge 40 of the vane 12 and is forced around the vane 12. The leading edge 40 has a span 42 extending from an inner diameter wall 62 of the duct 20 (0% span) to an outer diameter wall 64 of the duct 20 (100% span). Downstream of the leading edge 40, the airflow 30 encounters a trailing edge 50 of the vane 12 as the airflow 30 passes the vane 12. The trailing edge 50 of the vane 12 has a trailing edge span 52 extending from the inner diameter wall 62 (0% span) to the outer diameter wall 64 (100% span). The axial length of the vane 12 is referred to as the axial chord length 60.

[0035] Each vane 12 is in the vane assembly 10 has an aspect ratio that defines features of the vane. The aspect ratio is dependent on the length 42 of leading edge 40 span, the length of the trailing edge 50 span 52, and the length of the axial chord and is defined as being: Aspect Ratio = (leading edge span 42 + trailing edge span 52)/(2*axial chord 60). In the illustrated example, the aspect ratio is approximately 1.5. In alternate examples, the aspect ratio is less than 1.5.

[0036] Due to the circumferential vane 12 arrangement of the vane assembly 10, the features of each vane 12 define a throat distance between each vane 12 and each adjacent vane 12 at any given span of the vanes 12. The throat distance is the shortest single span distance from one vane 12 to an adjacent vane 12 in the vane assembly 10. The throat distance, as well as the throat angle, varies depending on the span. Thus, the throat distance and the throat angles of the vane assembly 10 will vary depending on what span percentage is being measured.

[0037] Figure 2 illustrates a top view of two vanes 110 in the stationary vane assembly 10 illustrated in figure 1. Each of the vanes 110 has a leading edge 140 that initially contacts the airflow 30 (illustrated in Figure 1). As the airflow 30 passes over the vanes 110 in the vane assembly 10, the contours of each individual vane 110 generate a pressure differential between the two sides of the vane 110. In the illustrated example vanes 110, the top side is a pressure side 112 and the bottom side of the vanes 110 is a suction side 114. The airflow immediately adjacent the suction side 112 has a pressure that is lower than the airflow immediately adjacent the pressure side 114.

[0038] As described above, the smallest distance between the two adjacent vanes 110, at a constant span percentage, is the throat distance 180. The throat distance at any given span percentage is uniquely defined by a single point on the suction side 112 of one vane 110 and a corresponding single point on the pressure side 114 of an adjacent vane 110. A line drawn along the throat distance 180 defines a throat angle 190 relative to a circumferential line 192 that is tangential to the trailing edge 150 of each of the vanes 110 within the vane assembly 10.

[0039] Figures 3a and 3b illustrate an outer diameter layer of a vane 210 at a span of 95-100% (Figure 3a) and a mid-span layer of the vane 210 at a span of 45-55% (Figure 3b). The tip, or 95-100% span region, is at the outer diameter endwall 64 of the duct 20. As with Figure 2, each of the illustrated vanes 210 includes a leading edge 240, a pressure side 212, a suction side 214, and a trailing edge 250. The throat distance 280 at the mid-span (Figure 3b) is shorter than the throat distance 280 at the tip (95-100% span). Similarly, the pressure side point defining the throat distance at the tip on each vane 210 is axially downstream from the pressure side point defining the throat distance 280 at mid-span on each vane 210. Because of this relationship, the throat angle 290 at mid-span is larger than the throat angle 290 at the tip, and airflow angle at the tip is opened up relative to airflow at mid- span.

[0040] Figure 4 illustrates an optional feature of the root portion (0-5% span) of the vanes 210 that can be included in the vane assembly illustrated in Figures 3a and 3b. The root, or 0-5% span region of the vane 210, is at the inner diameter endwall 62 of the duct 20. In the optional feature, the pressure side point defining the throat distance 280 at the root (0- 5% span) of the vane 210 is downstream of the pressure side point defining the throat distance 280 at mid-span (45-55% span). As a result of this feature, the throat angle 290 at mid-span of the vane 210 in the example of Figures 3a, 3b and 4 is larger than the throat angle 290 at either the tip (95-100% span) or the root (0-5% span), and the airflow at the outer diameter and the inner diameter is opened up relative to airflow at mid-span.

[0041] Figure 5 illustrates a chart showing the throat angles, with respect to percent span, of the example vane of Figure 3a, 3b without the inclusion of the feature of Figure 4 as line 410 and with the inclusion of the feature of Figure 4 as line 420. As can be seen by line 410, in the example not including the optional feature of Figure 4 the throat angle has a small decline as the percent span of the vane increases from 0% span 412 (the root of the vane) to mid-span 414, and then sharply declines from mid-span 414 to 100% span 416 (the tip of the vane). In the line 422, for the example where the optional feature of Figure 4 included, the throat angle starts with a low throat angle at 0% span 422 (the root of the vane) and increases until it reaches mid-span 424 (45-55% span), where the throat angle begins decreasing again until 100% span 426 (the tip).

[0042] In the example of Figure 4, the vanes 110, 210 are designed with relatively open throat angles near the root (inner diameter wall) and tip (outer diameter wall) and a relatively closed throat angle near the mid-span of the vane. By utilizing this varied throat angle configuration, the airflow along the end walls is increased relative to the flows at the mid- span line (where the throat angle is minimized). This airflow vortexing achieves a better flow distribution including more flow to the end wall regions of the duct 20. In one example implementation, the above described features are included in a vane assembly in a gas path of a jet engine.

[0043] Although a 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 vane assembly for a duct comprising:

a plurality of vanes arranged circumferentially about an axis defined by a duct;

wherein each of said plurality of vanes has a throat distance defining a shortest distance between the vane and an adjacent vane at a constant span;

wherein the throat distance defines a throat angle relative to a line tangential to a trailing edge of each of said plurality of vanes; and

wherein the throat angle of each vane at mid-span is greater than the throat angle at the tip region of each vane.

2. The vane assembly of claim 1, wherein said stationary duct has a duct angle of at least ten degrees, relative to the axis defined by the stationary duct.

3. The vane assembly of claim 1, wherein each vane in said plurality of vanes has an aspect ratio of less than or equal to 1.5.

4. The vane assembly of claim 1, wherein said plurality of vanes includes an even number of vanes.

5. The vane assembly of claim 1, wherein said plurality of vanes includes less than or equal to twenty vanes.

6. The vane assembly of claim 1, further comprising a root throat angle at a root region of the vane, wherein the root throat angle is less than the throat angle.

7. The vane assembly of claim 6, wherein the root throat angle is a throat angle measured at less than or equal to 5% span of the vane.

8. The vane assembly of claim 1, wherein the tip region throat angle is a throat angle measured at greater than or equal to 95% span of the vane.

9. The vane assembly of claim 1, wherein said mid-span throat angle is a smallest throat angle in a range of throat angles between 5% span and 95 % span.

10. The vane assembly of claim 9, wherein said mid-span throat angle is a smallest throat angle in a range of throat angles between 45% span and 55% span.

11. The vane assembly of claim 1 , wherein an airflow at an outer diameter of said vane assembly is elevated relative to an airflow at a mid-span region of the vane assembly.

12. The vane assembly of claim 11, wherein an airflow at an inner diameter of said vane assembly is elevated relative to an airflow at a mid-span region of the vane assembly.

13. A j et engine comprising :

a gas path duct having a vane assembly, wherein the vane assembly has a plurality of vanes arranged circumferentially about an axis defined by the gas path duct;

14. The jet engine of claim 12, wherein said gas path duct has a duct angle of at least ten degrees, relative to the axis defined by the gas path duct.

15. The jet engine of claim 13, wherein each of said plurality of vanes has an aspect ratio of less than or equal to 1.5.

16. The jet engine of claim 12, wherein said plurality of vanes is an even number of vanes.

17. The jet engine of claim 12, wherein said plurality of vanes is less than or equal to twenty vanes.

18. The jet engine of claim 13, wherein said plurality of vanes further define a root throat angle, wherein the root throat angle is less than the mid-span throat angle.

19. The jet engine of claim 18 wherein the root throat angle is a throat angle measured at less than or equal to 5% span of the vane.

20. The jet engine of claim 12, wherein the tip region throat angle is a throat angle measured at greater than or equal to 95% span of the vane.

21. The jet engine of claim 12, wherein said mid-span throat angle is a smallest throat angle in a range of throat angles between 5% span and 95 % span.

22. The jet engine of claim 21, wherein said mid-span throat angle is a smallest throat angle in a range of throat angles between 45% span and 55% span.

23. The jet engine of claim 13, wherein an airflow at an outer diameter of said vane assembly is elevated relative to an airflow at a mid-span region of the vane assembly.

24. The jet engine of claim 23, wherein an airflow at an inner diameter of said vane assembly is elevated relative to an airflow at the mid-span region of the vane assembly.