Compressor stator with contoured endwall

Patent metadata

Field	Value
Publication number	US-9879540-B2
Application number	US-201313795936-A
Country	US
Kind code	B2
Filing date	Mar 12, 2013
Priority date	Mar 12, 2013
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).

First claim

What is claimed is:

1. A compressor stator comprising:
a circumferential array of stator vanes; and
a radially inner shroud for supporting the stator vanes, the shroud having a circumferentially extending inner endwall exposed to an annular gas path of the compressor, the endwall having a circumferentially uniform, modified axial cross-sectional profile between the stator vanes, the modified axial cross-sectional profile comprising a concave deviation and a convex deviation from a nominal axial cross-sectional profile defining a baseline;
wherein the convex deviation has a maximum deviation from the nominal profile at a position corresponding to an axial position of a trailing edge of at least one of the vanes, the convex deviation being convex toward the annular gas path and extending from a first axial position on the inner endwall upstream of the trailing edge to a second axial position on the inner endwall downstream of the trailing edge.

2. The compressor stator as defined in claim 1 , wherein the concave deviation has a maximum deviation from the nominal profile at a position corresponding to an axial position of a maximum thickness of at least one of the vanes.

3. The compressor stator as defined in claim 2 , wherein the concave deviation has a maximum deviation from the nominal profile that is greater than 0.5% of a nominal chord of one of the vanes.

4. The compressor stator as defined in claim 1 , wherein the convex deviation has a maximum deviation from the nominal profile that is greater than 0.5% of a nominal chord of one of the vanes.

5. The compressor stator as defined in claim 1 , wherein the concave deviation has a maximum deviation from the nominal profile that is greater than 0.5% of a nominal chord of one of the vanes.

6. The compressor stator as defined in claim 1 , wherein the shroud comprises a plurality of slots formed in the endwall for receiving radial ends of the vanes.

7. A gas turbine engine comprising the compressor stator as defined in claim 1 .

8. The compressor stator as defined in claim 1 , wherein the concave deviation extends from one side of the nominal profile and the convex deviation extends from another side of the nominal profile.

9. A compressor stator comprising:
a circumferential array of stator vanes; and
a radially inner shroud for supporting the stator vanes, the shroud having a circumferentially extending inner endwall exposed to an annular gas path of the compressor, the endwall having a circumferentially uniform, modified axial cross-sectional profile between the stator vanes, the modified axial cross-sectional profile comprising at least one deviation from a nominal axial cross-sectional profile defining a baseline, the at least one deviation comprising:
a concave deviation having a maximum deviation from the nominal profile at a position corresponding to an axial position of a maximum thickness of at least one of the vanes; and
a convex deviation having a maximum deviation from the nominal profile at a position corresponding to an axial position of a trailing edge of the at least one of the vanes, the convex deviation being convex toward the annular gas path and extending from a first axial position on the inner endwall upstream of the trailing edge to a second axial position on the inner endwall downstream of the trailing edge.

10. The compressor stator as defined in claim 9 , wherein the concave deviation has a maximum deviation from the nominal profile that is greater than 0.5% of a nominal chord of one of the vanes.

11. The compressor stator as defined in claim 9 , wherein the shroud comprises a plurality of slots formed in the endwall for receiving radial ends of the vanes.

12. The compressor stator as defined in claim 9 , wherein the convex deviation is disposed axially downstream of the concave deviation.

13. The compressor stator as defined in claim 9 , wherein the convex deviation has a maximum deviation from the nominal profile that is greater than 0.5% of a nominal chord of one of the vanes.

14. The compressor stator as defined in claim 9 , wherein the concave deviation extends from one side of the nominal profile and the convex deviation extends from another side of the nominal profile.

Assignees

• Pratt & Whitney Canada

Inventors

• Li Yau-Wai
• Anand Karan
• Townsend Peter

Classifications

• F05D2250/711

  convex · CPC title

• F05D2250/712

  concave · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F01D9/04

  forming ring or sector · CPC title