Gas turbine engine flow path member

Patent metadata

Field	Value
Publication number	US-2016153284-A1
Application number	US-201514732153-A
Country	US
Kind code	A1
Filing date	Jun 5, 2015
Priority date	Dec 24, 2010
Publication date	Jun 2, 2016
Grant date	—

Abstract

A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.

First claim

What is claimed is:

1 . An apparatus comprising:
a gas turbine engine having a fluid cooled airfoil member disposed in a flow path and having a plurality of walls extending along a span of the member and enclosing an open interior, the walls forming a cooling passage therebetween, an inner wall of the plurality of walls extending into the flow path beyond a portion of an outer wall of the plurality of walls; and a plurality of apertures in the airfoil member having an upstream inlet and a downstream exit and operable to pass a fluid therethrough oriented to cool the inner wall that extends beyond the portion of the outer wall, wherein the downstream exits of the apertures are non-circular.

2 . The apparatus of claim 1 , wherein the inner wall forms a sacrificial rubbing member near the end of the airfoil member and used in case of contact with a surface of the flow path, wherein the inner wall extends radially away from the rubbing member past an end of the outer wall. The apparatus of claim 2 , wherein the fluid that passes through the plurality of apertures is air withdrawn from a portion of the gas turbine engine, wherein the inner wall includes a plurality of openings which communicate the fluid to the plurality of apertures from the open interior.

4 . The apparatus of claim 1 , wherein each of the plurality of openings are in communication with a corresponding one of the apertures of the plurality of apertures.

5 . The apparatus of claim 1 , wherein the plurality of apertures is oriented to pass fluid in a spanwise direction from a location between the inner wall and the outer wall, the inner wall forming a spar of the airfoil member and the outer wall forming a coversheet.

6 . The apparatus of claim 1 , wherein the inner wall includes openings through which cooling fluid is passed from the open interior into the cooling passage, wherein the outer wall includes cooling holes through which the cooling fluid from the open interior is passed, and wherein the portion of the outer wall is an end of the outer wall.

7 . The apparatus of claim 6 , which further includes a radial dam in the cooling passage to separate the cooling passage from the apertures.

8 . The apparatus of claim 1 , wherein the cooling passage is formed between a base of the inner member and an end of the outer member, the inner member not extending past an end of the outer member.

9 . An apparatus comprising:
a gas turbine engine having a rotatable turbomachinery component and a flow path through the rotatable turbomachinery component; an airflow member extending into the flow path and having a periphery that includes a pressure side, suction side, leading edge, and trailing edge; a contact member extending from an end of the airflow member to provide a sacrificial surface in case of contact of the airflow member with a wall of the flowpath; a recess surface between the contact member and the airflow member; and a plurality of apertures located in the recess surface and oriented to pass a cooling fluid, the plurality of apertures include exits adjacent to a surface of the contact member.

10 . The apparatus of claim 9 , wherein the contact member has a shape that follows the contours of the periphery, wherein the airflow member is disposed in a turbine of the gas turbine engine, and wherein the recess extends around the pressure side, suction side, leading edge, and trailing edge.

11 . The apparatus of claim 10 , wherein the plurality of apertures is arranged to pass the cooling fluid having a streamline in the radial direction.

12 . The apparatus of claim 9 , wherein the plurality of apertures have an upstream area smaller than a downstream area.

13 . The apparatus of claim 9 , wherein the airflow member includes a cooling pathway between an inner extending member and an outer extending member, the inner extending member forming the contact member.

14 . The apparatus of claim 13 , wherein the apertures are quadrilateral in shape and are formed between the inner extending member and the outer extending member.

15 . The apparatus of claim 13 , wherein the inner extending member is a spar and the outer extending member is a coversheet, the coversheet including a plurality of openings.

16 . The apparatus of claim 13 , which further includes an air flow dam positioned in the cooling pathway, the inner extending member including openings to permit a cooling fluid from an interior of the airflow member to pass into the cooling pathway, the outer extending member including openings to permit the cooling fluid to exit the air flow member.

17 . An apparatus comprising:
a gas turbine engine having a rotating component capable of altering a pressure of a flow stream through the rotating component; an airflow device positioned with the rotating component to pass a fluid flowing through the gas turbine engine; a rubbing tip set back from an edge of the airflow device and having a profile similar to the airflow device; and means for discharging a cooling fluid from the airflow device radially between the members.

18 . The apparatus of claim 17 , wherein the airflow device includes an inner radial member and an outer radial member, the inner radial member forming the rubbing tip, and which further includes means for transpiration cooling the airflow device.

19 . A method comprising:
operating a gas turbine engine; conveying a working fluid through a flow path of the gas turbine engine in which the working fluid encounters an airfoil member disposed in the flow path, the airfoil member having an inner member extending along the span of the airfoil member and overhanging an end of the outer member, the inner member having an end radially away from the overhanging end and past the end of the outer member; flowing a cooling fluid from an interior of the airfoil member to a cooling space radially away from of the end of the outer member between the inner member and the outer member; and admitting a cooling fluid to the overhanging portion of the inner member via a passage from the interior of the airfoil member.

20 . The method of claim 19 , wherein the flowing further includes encountering a radial dam disposed between the cooling space and the cooling fluid admitted to the overhanging portion.

21 . The method of claim 19 , wherein the airfoil member is a laminated construction.

22 . The method of claim 19 , which further includes transpiration cooling the airfoil member.

23 . The method of claim 19 , wherein the admitting further includes diffusing the cooling fluid.

24 . The method of claim 19 , which further includes impingement cooling the outer member.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Kwon Okey
• Rhodes Jeffrey F

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title