Stator assembly including bleed ports for turbine engine compressor

• US 20090000306A1
• Filed: 09/13/2007
• Published: 01/01/2009
• Est. Priority Date: 09/14/2006
• Status: Active Grant

• Current Assignee: Caterpillar Incorporated, Solar Turbines Incorporated (Caterpillar Incorporated)
• Original Assignee: Solar Turbines Incorporated (Caterpillar Incorporated)
• Inventors: Adjan, Bachar, Fregoe, Jerry Mar Philip, Damle, Sachin V.
• Granted Patent: US 8,292,567 B2
• Time in Patent Office: Days
• US Class Current: 60/785
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F04D 27/023 Details or means for fluid extraction
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A stator assembly for a turbine engine is disclosed. The stator assembly has a stator support ring, a plurality of stator vanes protruding radially inwardly from the stator support ring, and at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes. The at least one bleed port defines an oblong profile having a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes, and a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes. The profile may be concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

Claims

1. A stator assembly for a turbine engine, the stator assembly comprising:

a stator support ring;

a plurality of stator vanes protruding radially inwardly from the stator support ring; and

at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes, wherein the at least one bleed port defines an oblong profile, the profile comprising;

a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes; and

a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes,

wherein the profile is concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

2. The stator assembly of claim 1, wherein the first end is proximate a pressure sidewall of the first stator vane of the at least two adjacent stator vanes, and the second end is proximate the suction sidewall of the second stator vane of the at least two adjacent stator vanes.

3. The stator assembly of claim 1, wherein the first end defines a predetermined curve.

4. The stator assembly of claim 1, wherein the second end is substantially linear.

5. The stator assembly of claim 1, wherein the first end is upstream from the second end with respect to a direction of airflow, and the profile extends from the leading edge of the first stator vane of the at least two adjacent stator vanes and the trailing edge of the second stator vane of the at least two adjacent stator vanes.

6. The stator assembly of claim 1, wherein the profile is convex toward a pressure sidewall of the first stator vane of the at least two adjacent stator vanes.

7. The stator assembly of claim 1, wherein a shape of the profile is substantially in accordance with Cartesian coordinates set forth in Table I or Table II, carried only to four decimal places, within a tolerance of one ten-thousandth, and smoothly interconnected to form a complete bleed port shape.

8. A compressor for a turbine engine, the compressor comprising:

a casing;

at least one rotor assembly encompassed by the casing; and

at least one stator assembly disposed downstream from the rotor assembly and encompassed by the casing, the stator assembly comprising;

a stator support ring;

a plurality of stator vanes protruding radially inwardly from the stator support ring; and

at least one bleed port disposed on the stator support ring between at least two adjacent stator vanes of the plurality of stator vanes, wherein the at least one bleed port defines an oblong profile, the profile comprising;

a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes; and

a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes,

wherein the profile is concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

9. The compressor of claim 8, wherein the first end is proximate a pressure sidewall of the first of the at least two adjacent stator vanes, and the second end is proximate the suction sidewall of the second of the at least two adjacent stator vanes.

10. The compressor of claim 8, wherein the first end defines a predetermined curve.

11. The compressor of claim 8, wherein the second end is substantially linear.

12. The compressor of claim 8, wherein the first end is upstream from the second end with respect to a direction of airflow.

13. The compressor of claim 8, wherein the profile is convex toward a pressure sidewall of the first of the at least two adjacent stator vanes.

14. The compressor of claim 8, wherein a shape of the profile is substantially in accordance with Cartesian coordinates set forth in Table I or Table II, carried only to four decimal places, and smoothly interconnected to form a complete bleed port shape.

15. The compressor of claim 8, further including a bleed plenum over the at least one bleed port between a radially inner surface of the casing and a radially outer surface of the stator support ring, wherein the bleed plenum is in fluid communication with the at least one bleed port.

16. A segment of stator assembly having a vane member protruding from a stator support ring member, wherein:

a first side of the stator support ring member defines a first portion of a first bleed port,

a second side of the stator support ring member opposite the first side of the stator support ring member defines a second counterpart portion of a second bleed port adjacent to the first bleed port,

the first portion of the first bleed port defines a first end terminating near a trailing edge of the vane member,

the second counterpart portion of the second bleed port defines a second end terminating near a leading edge of the vane member,

the first portion of the first bleed port is concave toward a suction sidewall of the vane member, and

the second counterpart portion of the second bleed port is convex toward a pressure sidewall of the vane member.

17. The segment of claim 16, wherein the first end is proximate a suction sidewall of the vane member, and the second end is proximate a pressure sidewall the vane member.

18. The segment of claim 16, wherein the first end is substantially linear, and the second end defines a predetermined curve.

19. The segment of claim 16, wherein a shape of the first and second bleed port is substantially in accordance with Cartesian coordinates set forth in Table I or Table II, carried only to three decimal places, and smoothly interconnected to form a complete bleed port shape.

20. The segment of claim 16, wherein the vane member is substantially perpendicular to the stator support ring.

21. The segment of claim 16, wherein the vane member and the stator support ring are integrally formed.

22. The segment of claim 16, wherein the vane member is fixedly attached to the stator support ring.

23. A stator assembly for a turbine engine compressor, the stator assembly comprising a plurality of segments as in claim 16, annularly arranged to form a stator assembly having a plurality of vanes protruding radially inwardly, such that at least one bleed port is formed between at least two adjacent vanes of the plurality of vanes.

24. A method of bleeding air in a turbine engine, comprising:

bleeding compressed air through at least one port located between at least two of a plurality of adjacent stator vanes, wherein the at least one port defines an oblong profile, the profile comprising;

a first end terminating near a leading edge of a first stator vane of the at least two adjacent stator vanes; and

a second end, substantially opposed from the first end, terminating near a trailing edge of a second stator vane of the at least two adjacent stator vanes,

wherein the profile is concave toward a suction sidewall of the second stator vane of the at least two adjacent stator vanes.

25. The method of claim 24, wherein a shape of the profile is substantially in accordance with Cartesian coordinates set forth in Table I or Table II, carried only to four decimal places, within a tolerance of one ten-thousandth, and smoothly interconnected to form a complete bleed port shape.