Segmented clearance control ring

Patent metadata

Field	Value
Publication number	US-10280782-B2
Application number	US-201314759317-A
Country	US
Kind code	B2
Filing date	Feb 26, 2013
Priority date	Feb 26, 2013
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.

First claim

What is claimed is:

1. A clearance control ring for a rotor, comprising:
a first control ring segment
a second control ring segment interlocked with the first control ring segment to form a full hoop clearance control ring, each segment of the clearance control ring having a forked end and a slotted end, each forked end interlocking with the slotted end of an adjacent segment to form a joint of the full hoop; and
a plurality of carriers mounted onto the clearance control ring and a plurality of seals are mounted on the carriers.

2. The clearance control ring of claim 1 , wherein the carriers are slidably mounted onto the clearance control ring.

3. The clearance control ring of claim 1 , wherein each seal is unitary with a carrier.

4. The clearance control ring of claim 1 , further including a bridge between each pair of control ring segments and a fastener securing each bridge to one interlocked pair of the control ring segments.

5. The clearance control ring of claim 1 , further comprising: a fastener that extends through the joint to secure the forked end and the slotted end.

6. A gas turbine engine, comprising:
a rotor having a plurality of radially outwardly extending blades;
a clearance control ring surrounding the radially extending blades of the rotor, the clearance control ring being segmented into at least two segments, each segment of the clearance control ring having a forked end interlocking with a slotted end of an adjacent segment to form a joint; and
a fastener that extends through the joint.

7. The engine of claim 6 , wherein the rotor is provided in a compressor stage of the engine.

8. The engine of claim 6 , wherein the rotor is provided in a turbine stage of the engine.

9. The engine of claim 6 , wherein the rotor includes multiple stages aligned axially along the engine and a separate clearance control ring surrounds each stage, each clearance control ring being segmented into at least two segments.

10. The engine of claim 6 , wherein the engine further comprises:
a plurality of carriers mounted onto the clearance control ring; and
a plurality of seals, each seal being mounted on one of the carriers.

11. The engine of claim 10 , wherein the carriers are slidably mounted onto the clearance control ring.

12. The engine of claim 10 , wherein each seal is unitary with one of the carriers.

13. The engine of claim 6 , wherein the rotor and clearance control ring are surrounded by a split case.

14. A method of assembling a clearance control ring into a gas turbine engine, comprising:
positioning a first control ring segment proximate a rotor of the gas turbine engine;
interlocking a second segment of the clearance control ring with the first segment of the clearance control ring to create a joint between the adjacent segments of the clearance control ring;
inserting a fastener through the joint;
continuing the interlocking step until a full hoop clearance control ring circumscribes the engine rotor; and
securing a case of the engine around the assembled clearance control ring.

15. The method of claim 14 , further comprising mounting a plurality of carriers on the clearance control ring and mounting a seal on each carrier.

16. The method of claim 15 , wherein mounting the carriers on the clearance control ring entails sliding the carriers onto the segments of the clearance control ring.

17. The method of claim 14 , further comprising mounting a plurality of unitary carriers and seals on the clearance control ring.

18. The method of claim 14 , further comprising loading the clearance control ring to prevent ovalization and disengagement of the segments of the clearance control ring.

19. The method of claim 14 , further comprising inserting a bridge and a fastener through each joint of the clearance control ring.

Assignees

• United Technologies Corp

Inventors

• Mccaffrey Michael G
• Garcia Igor S
• Farris John R
• Pelletier Brian R
• Almy Thomas
• Rouse Brandon T
• Borja Mark

Classifications

• B23P19/00

  Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation {(connecting metal parts or objects by metal-working procedures B21J, B23K)}; Tools or devices therefor so far as not provided for in other classes (hand tools in general B25) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• Y10T29/49325

  Shaping integrally bladed rotor · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D9/04

  forming ring or sector · CPC title