Variable thickness trailing edge cavity and method of making

Patent metadata

Field	Value
Publication number	US-2016017724-A1
Application number	US-201414781732-A
Country	US
Kind code	A1
Filing date	Mar 21, 2014
Priority date	Apr 3, 2013
Publication date	Jan 21, 2016
Grant date	—

Abstract

A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture.

First claim

1 . A method for forming an airfoil, the method comprising:
forming a ceramic core; forming a refractory metal core using additive manufacturing, wherein the refractory metal core has an upstream end and a downstream end, and wherein the upstream end has a lateral thickness greater than a lateral thickness of the downstream end; joining the ceramic core and the refractory metal core to form a hybrid core; and casting the airfoil around the hybrid core, wherein the ceramic core is used to define an internal cavity of the airfoil, and wherein the refractory metal core is used to define a trailing edge cavity within the airfoil, the trailing edge cavity being in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge.

2 . The method of claim 1 , wherein the refractory metal core extends from an inner radial end to an outer radial end, and wherein the inner radial end has an average lateral thickness greater than an average lateral thickness of the outer radial end.

3 . The method of claim 1 , wherein the refractory metal core extends from an inner radial end to an outer radial end, and wherein the outer radial end has an average lateral thickness greater than an average lateral thickness of the inner radial end.

4 . The method of claim 1 , wherein the refractory metal core is formed using a technique selected from the group consisting of direct metal laser sintering, electron beam machining, selective laser sintering, laminated object manufacturing and combinations thereof.

5 . The method of claim 1 , wherein the refractory metal core comprises an attachment structure that is received by the ceramic core during joining of the ceramic core and the refractory metal core.

6 . A hybrid core comprising:
a ceramic core for forming an internal cavity within an airfoil; a refractory metal core for forming a trailing edge slot within the airfoil, the refractory metal core comprising:
an upstream end extending from an inner radial end to an outer radial end;
a downstream end generally opposite the upstream end and extending from an inner radial end to an outer radial end, wherein the upstream end has a first thickness at a given radial location and the downstream end has a second thickness at the given radial location and wherein the first thickness is generally greater than the second thickness at the given radial location.

7 . The hybrid core of claim 6 , wherein the second thickness of the downstream end of the refractory metal core at an innermost radial location is greater than the second thickness of the downstream end of the refractory metal core at an outermost radial location.

8 . The hybrid core of claim 6 , wherein the second thickness of the downstream end of the refractory metal core at an outermost radial location is greater than the second thickness of the downstream end of the refractory metal core at an innermost radial location.

9 . The hybrid core of claim 6 , wherein the refractory metal core further comprises an attachment structure for connecting the refractory metal core to the ceramic core.

10 . The hybrid core of claim 9 , wherein the attachment structure comprises a projection, and wherein the ceramic core comprises an opening complimentary to the projection for receiving the attachment structure.

11 . An airfoil comprising:
a leading edge; a trailing edge; a pressure side wall extending from the leading edge to the trailing edge; a suction side wall extending from the leading edge to the trailing edge generally opposite the pressure side wall; an internal cavity located between the pressure side wall and the suction side wall; a trailing edge cavity extending downstream from the internal cavity between the pressure side wall and the suction side wall, the trailing edge cavity comprising:
an upstream end; and
a downstream end, wherein a first distance measured between the pressure side wall and the suction side wall at the upstream end is greater than a second distance measured between the pressure side wall and the suction side wall at the downstream end.

12 . The airfoil of claim 11 , wherein the trailing edge cavity extends from an inner radial location to an outer radial location, and wherein a third distance measured between the pressure side wall and the suction side wall at the upstream end at an innermost radial location is greater than a fourth distance measured between the pressure side wall and the suction side wall at the upstream end at an outermost radial location.

13 . The airfoil of claim 11 , wherein the trailing edge cavity extends from an inner radial location to an outer radial location, and wherein a third distance measured between the pressure side wall and the suction side wall at the upstream end at an innermost radial location is less than a fourth distance measured between the pressure side wall and the suction side wall at the upstream end at an outermost radial location.

14 . The airfoil of claim 12 , wherein the airfoil is part of a component selected from the group consisting of a blade and a vane.

15 . The airfoil of claim 13 , wherein the airfoil is part of a component selected from the group consisting of a blade and a vane.

16 . A method for forming a hybrid core used to cast an airfoil, the method comprising:
forming a refractory metal core that is used to define a trailing edge cavity within the airfoil using additive manufacturing, wherein the refractory metal core has an upstream end and a downstream end, and wherein the upstream end has a lateral thickness greater than a lateral thickness of the downstream end; and forming a ceramic core that is used to define an internal cavity of the airfoil.

17 . The method of claim 16 , further comprising:
joining the ceramic core and the refractory metal core.

18 . The method of claim 16 , wherein the refractory metal core extends from an inner radial end to an outer radial end, and wherein the inner radial end has an average lateral thickness greater than an average lateral thickness of the outer radial end.

19 . The method of claim 16 , wherein the refractory metal core extends from an inner radial end to an outer radial end, and wherein the outer radial end has an average lateral thickness greater than an average lateral thickness of the inner radial end.

20 . The method of claim 17 , wherein the refractory metal core comprises an attachment structure that is received by the ceramic core during joining of the ceramic core and the refractory metal core.

Assignees

• United Technologies Corp

Inventors

• Xu Jinquan

Classifications

• B22F5/04 Primary

  of turbine blades · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2230/13

  using lasers · CPC title