Radial position control of case support structure with splined connection

Patent metadata

Field	Value
Publication number	US-2016153306-A1
Application number	US-201414904621-A
Country	US
Kind code	A1
Filing date	Jun 18, 2014
Priority date	Jul 23, 2013
Publication date	Jun 2, 2016
Grant date	—

Abstract

A radial position control assembly for a gas turbine engine includes a case structure. A support structure is operatively supported by the case structure respectively with first and second splines in engagement with one another. The support structure includes an annular recess, and a support ring is received in the recess. The support structure and the support ring having different coefficients of thermal expansion. An axial biasing member urges the first and second splines into engagement with one another.

First claim

What is claimed is:

1 . A radial position control assembly for a gas turbine engine comprising:
a case structure; a support structure operatively supported by the case structure respectively with first and second splines engaging one another, the support structure including an annular recess; a support ring received in the recess, the support structure and the support ring having different coefficients of thermal expansion; and an axial biasing member urging the first and second splines into engagement with one another.

2 . The radial position control assembly according to claim 1 , wherein the first and second splines include beveled surfaces that slidably engage one another, the axial biasing member and the first and second splines on opposing axial sides of the support structure.

3 . The radial position control assembly according to claim 1 , wherein the support structure includes first and second portions providing the recess and secured about the support ring.

4 . The radial position control assembly according to claim 1 , comprising a sealing structure adjacent to the support structure, the support ring maintaining the support structure relative to the sealing structure at a radial clearance during thermal transients based upon a circumferential gap between adjacent support structure and based upon a radial gap between the support ring and the support structure.

5 . The radial position control assembly according to claim 4 , wherein the support structure is a blade outer air seal and the sealing structure is a blade.

6 . The radial position control assembly according to claim 4 , wherein the case structure is a compressor case, and the support structure is an outer platform of a vane.

7 . The radial position control assembly according to claim 4 , wherein the coefficient of thermal expansion of the support ring is less than the coefficient of thermal expansion of the support structure, and the support ring is a continuous circumferentially unbroken annular structure.

8 . The radial position control assembly according to claim 7 , wherein the support ring includes first and second states, and the support structure includes expanded and contracted positions in each of the first and second states of the support ring, wherein the circumferential gap is about zero in the expanded state and the circumferential gap is greater than zero in the contracted state, wherein the support ring is enlarged in the second state with respect to the first state, the support structure and support ring respectively include first and second surfaces that are radially adjacent to one another to provide the radial gap, and the radial gap is about zero in first and fourth conditions, the first condition with the support ring in the first state and the support structure contracted, and the fourth condition with the support ring in the second state and the support structure contracted, the radial gap greater than zero in second and third conditions, the second condition with the support ring in the first state and the support structure expanded, and the third condition with the support ring in the second state and the support structure expanded.

9 . The radial position control assembly according to claim 8 , wherein the first condition corresponds to a cold condition, the second condition corresponds to a warm condition, the third condition corresponds to a hot condition, and the fourth condition corresponds to a rapid deceleration condition from the hot condition.

10 . The radial position control assembly according to claim 1 , comprising a radial biasing member arranged between the case structure and the support structure providing a radial biasing force to the support structure.

11 . A gas turbine engine comprising:
a compressor section; a combustor fluidly connected downstream from the compressor section; a turbine section fluidly connected downstream from the combustor; a case structure disposed about the compressor section, the combustor and the turbine section; a support structure having multiple segments operatively supported by the case structure respectively with first and second splines engaging one another, the support structure including an annular recess; a support ring received in the recess, the support structure and the support ring having different coefficients of thermal expansion; a sealing structure adjacent to the support structure, the support ring maintaining the support structure relative to the sealing structure at a radial clearance during thermal transients based upon a circumferential gap between adjacent support structure segments and based upon a radial gap between the support ring and the support structure; and an axial biasing member urging the first and second splines into engagement with one another while accommodating misalignment between the first and second splines from non-uniform circumferential gaps between the segments.

12 . The gas turbine engine according to claim 11 , wherein the first and second splines include beveled surfaces that slidably engage one another.

13 . The gas turbine engine according to claim 11 , wherein the support structure includes first and second portions providing the recess and secured about the support ring.

14 . The gas turbine engine according to claim 11 , wherein the support structure is a blade outer air seal and the sealing structure is a blade.

15 . The gas turbine engine according to claim 11 , wherein the case structure is a compressor case, and the support structure is an outer platform of a vane.

16 . The gas turbine engine according to claim 11 , wherein the coefficient of thermal expansion of the support ring is less than the coefficient of thermal expansion of the support structure, and the support ring is a continuous circumferentially unbroken annular structure.

17 . The gas turbine engine according to claim 16 , wherein the support ring includes first and second states, and the support structure includes expanded and contracted positions in each of the first and second states of the support ring, wherein the circumferential gap is about zero in the expanded state and the circumferential gap is greater than zero in the contracted state, wherein the support ring is enlarged in the second state with respect to the first state, the support structure and support ring respectively include first and second surfaces that are radially adjacent to one another to provide the radial gap, and the radial gap is about zero in first and fourth conditions, the first condition with the support ring in the first state and the support structure contracted, and the fourth condition with the support ring in the second state and the support structure contracted, the radial gap greater than zero in second and third conditions, the second condition with the support ring in the first state and the support structure expanded, and the third condition with the support ring in the second state and the support structure expanded.

18 . The gas turbine engine according to claim 17 , wherein the first condition corresponds to a cold condition, the second condition corresponds to a warm condition, the third condition corresponds to a hot condition, and the fourth condition corresponds to a rapid deceleration condition from the hot condition.

19 . The gas turbine engine according to claim 11 , comprising a radial biasing member arranged between the case structure and the support structure providing a radial biasing force to the support structure.

Assignees

• United Technologies Corp

Inventors

• Romanov Dmitrity A
• Duguay Brian

Classifications

• F05D2250/291

  hollowed · CPC title

• F05D2250/23

  prismatic · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F05D2240/55

  Seals · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title