Stress Reduction For Film Cooled Gas Turbine Engine Component

Patent metadata

Field	Value
Publication number	US-2016153282-A1
Application number	US-201514707409-A
Country	US
Kind code	A1
Filing date	May 8, 2015
Priority date	Jul 11, 2014
Publication date	Jun 2, 2016
Grant date	—

Abstract

A component for a gas turbine engine includes a highly conductive film cooled component with a leading edge area and a trailing edge area, the leading edge area including a multiple of film holes spaced to reduce a thermal gradient between the leading edge area and the trailing edge area to below about 200 F (93 C).

First claim

What is claimed:

1 . A component for a gas turbine engine, comprising:
a highly conductive film cooled component with a leading edge area and a trailing edge area, including a multiple of film holes in a film hole region, each of said multiple of film holes spaced one to another to reduce a thermal gradient aft of said film hole region to below about 200 F (93 C).

2 . The component as recited in claim 1 , wherein said component is manufactured of Molybdenum.

3 . The component as recited in claim 1 , wherein said highly conductive film cooled component is manufactured of a Monolithic ceramic.

4 . The component as recited in claim 1 , wherein said leading edge area and said trailing edge area define a chord of a component.

5 . The component as recited in claim 4 , wherein said multiple of film holes are arranged in a row transverse to said chord.

6 . The component as recited in claim 1 , wherein said multiple of film holes provide a coverage of between about 15%-75%.

7 . The component as recited in claim 6 , wherein said multiple of film holes provide a coverage of between about 40%-60%.

8 . The component as recited in claim 1 , wherein said multiple of film holes provide a ligament distance greater than about 0.050 in (1.27 mm).

9 . The component as recited in claim 1 , wherein each of said multiple of film holes define a pitch to diameter (P/D) ratio greater than about 2.2.

10 . The component as recited in claim 9 , wherein each of said multiple of film holes define a pitch to diameter (P/D) ratio greater than about 4.

11 . A component for a gas turbine engine, comprising:
a highly conductive film cooled component with a thermal conductivity greater than about 150 BTU (IT)-inch/hour/square foot/° F. and a row of multiple film holes that provide a coverage between about 15%-75%.

12 . The component as recited in claim 11 , wherein said multiple of film holes provide a coverage of between about 40%-60%.

13 . The component as recited in claim 11 , wherein said multiple of film holes provide a ligament distance greater than about 0.050 in (1.27 mm).

14 . The component as recited in claim 13 , wherein each of said multiple of film holes define a pitch to diameter (P/D) ratio greater than about 2.2.

15 . The component as recited in claim 14 , wherein each of said multiple of film holes define a pitch to diameter (P/D) ratio greater than about 4.

16 . The component as recited in claim 14 , wherein said multiple of film holes reduces a thermal gradient between a film hole region with said of multiple film holes and a trailing edge area aft thereof to below about 200 F (93 C).

17 . A method of cooling a film cooled component for a gas turbine engine, comprising:
arranging at least one row of a multiple of film holes proximate a leading edge area of a highly conductive film cooled component to control a thermal gradient aft of said multiple of film holes such that a stress from the thermal gradient is below a predetermined acceptable stress.

18 . The method as recited in claim 17 , wherein the thermal gradient is below about 200 F (93 C).

19 . The method as recited in claim 17 , wherein the arranging further comprises providing a ligament distance between each of the multiple of film holes with respect to a thermal conductivity of a material of the highly conductive film cooled component.

20 . The method as recited in claim 19 , wherein the thermal conductivity of said material is at least about 300% that of a nickel superalloy.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W

Classifications

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F05D2300/131

  Molybdenum · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2240/304

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

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title