Case with vane retention feature

Patent metadata

Field	Value
Publication number	US-9790806-B2
Application number	US-201514731676-A
Country	US
Kind code	B2
Filing date	Jun 5, 2015
Priority date	Jun 6, 2014
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis. The assembly further includes an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis.

First claim

What is claimed is:

1. An assembly for a gas turbine engine having an engine axis, the assembly comprising:
a case including an integrally formed projection configured to extend transverse to the engine axis; and
a stator vane including a flange configured for contact with the projection to limit motion of the stator vane along the engine axis, wherein the flange is positioned axially between the case and the projection, and wherein an aft surface of the flange and a fore surface of the projection are configured for contacting one another along an inclined interface relative to the engine axis.

2. The assembly as recited in claim 1 , wherein the case and the projection are monolithically formed.

3. The assembly as recited in claim 1 , wherein the stator vane includes a platform having the flange.

4. The assembly as recited in claim 1 , further comprising a plurality of rotor blades downstream of the stator vane.

5. The assembly as recited in claim 1 , wherein an aft surface of the flange is configured to contact a fore surface of the projection.

6. The assembly as recited in claim 1 , wherein the case is configured to be mounted adjacent a low pressure compressor and a high pressure compressor of the engine.

7. An assembly for a gas turbine engine having an engine axis, the assembly comprising:
a case including an integrally formed projection configured to extend transverse to the engine axis; and
an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis, wherein an aft surface of the flange is configured to contact a fore surface of the projection, and wherein the aft surface of the flange and the fore surface of the projection are configured for contacting one another along an inclined interface relative to the engine axis.

8. The assembly as recited in claim 7 , wherein the inclined interface is inclined at an acute angle relative to the engine axis.

9. A case for a gas turbine engine having an engine axis, the case comprising:
a stop monolithically formed with the case and configured to circumferentially extend about the engine axis with a fore surface of the stop oriented at an angle relative to the engine axis, wherein the stop is oriented at an acute angle relative to the engine axis.

10. The case as recited in claim 9 , wherein the stop extends from a main body of the case to a free end.

11. The case as recited in claim 9 , wherein the stop is configured to contact a flange of an engine component to limit axial movement thereof.

12. A component for a gas turbine engine having an engine axis, the component comprising:
an inner platform including a flange, the flange projecting from a radially inner surface of the inner platform, wherein the flange is configured to be mounted in the engine with an aft surface thereof inclined at an acute angle relative to the engine axis.

13. The component as recited in claim 12 , wherein the component is a variable area vane.

14. The component as recited in claim 13 , wherein the vane includes
an airfoil section;
a root section; and
a bushing adjacent the root section, the bushing configured to radially retain the root section while allowing rotation of the root section.

15. The component as recited in claim 14 , wherein the root section is configured for rotation about an axis normal to the engine axis.

16. The component as recited in claim 12 , wherein the flange is configured to contact a retainer of a case.

Assignees

• United Technologies Corp

Inventors

• Champion Nathan F
• Mattia Stephen H

Classifications

• F01D21/04

  responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title

• F01D9/041

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

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title