Claims
- 1. A high pressure compressor front frame of a gas turbine engine having a longitudinal axis, said frame comprising:a plurality of struts therein, each of said struts comprising a main body having a coolant flow passage therethrough; a plurality of fins extending from an external surface of said main body, each said fin comprising an upstream end; and at least one opening defined in a peripheral portion of said frame for channeling bleed flow therethrough, at least some of said fin upstream ends being positioned in different axial locations to facilitate enhanced bleed flow to said opening.
- 2. A high pressure compressor front frame in accordance with claim 1 wherein said coolant flow passage is an inner passage formed by an inner member positioned within an outer member.
- 3. A high pressure compressor front frame in accordance with claim 2 wherein said inner member has a plurality of impingement holes therethrough.
- 4. A high pressure compressor front frame in accordance with claim 3 wherein coolant may flow through said inner member impingement holes and into a space between inner and outer members.
- 5. A high pressure compressor front frame in accordance with claim 1 wherein said coolant flow passage is formed by a plurality of radial openings in said strut.
- 6. A high pressure compressor front frame in accordance with claim 1 wherein said coolant flow passage is a hollow cavity extending at least partially through said strut.
- 7. A high pressure compressor front frame in accordance with claim 6 wherein a plurality of turbulators are positioned on an interior surface of said hollow cavity.
Parent Case Info
This application is a divisional of Ser. No. 08/955,799,now U S. Pat. No. 6,430,931 filed Oct. 22, 1997, which is hereby incorporated by reference.
US Referenced Citations (20)