Vane carrier assembly

Patent metadata

Field	Value
Publication number	US-9835171-B2
Application number	US-85990410-A
Country	US
Kind code	B2
Filing date	Aug 20, 2010
Priority date	Aug 20, 2010
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A vane carrier assembly is provided for supporting vanes within a main engine casing of a gas turbine engine. The vane carrier assembly comprises a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly. The support panels are assembled such that the support panels expand circumferentially to minimize radial expansion of the vane support assembly during operation of the gas turbine engine. A control ring is coupled to the main engine casing, and the vane support assembly is coupled to the control ring. The control ring may be formed from a material having a coefficient of thermal expansion less than that of the material from which the vane support assembly is formed.

First claim

What is claimed is:

1. A vane carrier assembly for supporting vanes within a main engine casing of a gas turbine engine, said vane carrier assembly comprising:
a plurality of vane support panels positioned adjacent to one another so as to define a vane support assembly, said support panels being assembled such that said support panels expand circumferentially to minimize radial expansion of said vane support assembly during operation of the gas turbine engine, said support panels extending over at least one row of blades; and
a control ring loosely coupled to the main engine casing, said vane support assembly being coupled to said control ring,
wherein said plurality of vane support panels are made from a first material and said control ring is made from a second material, wherein said second material is thermally more stable than said first material.

2. The vane carrier assembly of claim 1 , wherein said control ring is supported by the main engine casing such that the main engine casing is capable of moving radially relative to said control ring.

3. The vane carrier assembly of claim 1 , wherein said first material has a coefficient of thermal expansion greater than that of said second material.

4. The vane carrier assembly of claim 1 , wherein said first material is formed from a steel alloy.

5. The vane carrier assembly of claim 1 , wherein said second material is formed from a nickel-iron-cobalt alloy.

6. The vane carrier assembly of claim 1 , wherein said control ring has a radial dimension which is greater than an axial dimension.

7. The vane carrier assembly of claim 1 , wherein control ring has an axial dimension which is greater than a radial dimension.

8. The vane carrier assembly of claim 1 , wherein each of said vane support panels extends generally circumferentially in response to thermal expansion and contraction during operation of said gas turbine engine.

9. The vane carrier assembly of claim 1 , wherein said control ring is formed from a low thermal coefficient of expansion material to generally minimize thermal expansion and contraction of said control ring in a radial direction.

10. The vane carrier assembly of claim 1 , wherein said control ring and support panels are coupled so as to move radially together.

11. A method of controlling clearance between tips of rotating blades and an inner surface of a vane support assembly within an engine casing of a gas turbine engine, said method comprising:
providing a plurality of vane support panels positioned adjacent to one another to define the vane support assembly, the panels being made of a first material and extending over at least one row of blades;
providing a control ring adapted to be supported by the engine casing for movement relative to the engine casing and made of a second material; and
securing said vane support assembly to said control ring, wherein said second material is thermally more stable than said first material.

12. The method of claim 11 , wherein said first material has a coefficient of thermal expansion greater than that of said second material.

13. A vane carrier assembly for supporting vanes within a main engine casing of a gas turbine engine, said vane carrier assembly comprising:
a vane support assembly comprising a plurality of vane support panels positioned adjacent to one another, each of said support panels comprising a first section and a second section, said panel second sections being formed from a first material and said panel first sections and a control ring being formed from a second material, said first material having a coefficient of thermal expansion greater than that of said second material; and
said control ring loosely coupled to the main engine casing such that the main engine casing is capable of moving radially relative to said control ring, said vane support assembly being coupled to said control ring.

14. The vane carrier assembly of claim 13 , wherein said first material is formed from a steel alloy.

15. The vane carrier assembly of claim 13 , wherein said second material is formed from a nickel-iron-cobalt alloy.

16. The vane carrier assembly of claim 13 , wherein said control ring and support panels are coupled so as to move radially together.

Assignees

• Kimmel Keith D
• Wilson Jack
• Siemens Energy Inc

Inventors

• Kimmel Keith D
• Wilson Jack

Classifications

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D29/541 Primary

  Specially adapted for elastic fluid pumps (F04D29/56 takes precedence) · CPC title

• F01D11/18

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F01D9/041

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