Passive control of gas turbine clearances using ceramic matrix composites inserts

• US 11,391,173 B2
• Filed: 10/29/2019
• Issued: 07/19/2022
• Est. Priority Date: 06/11/2013
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Mondal, Bhaskar Nanda, Rahaim, John Joseph, Moniz, Thomas, Ross, Steven A., Kirk, Joel, Hunter, Scott, Fusinato, Daniel
• Primary Examiner(s): Hasan, Sabbir
• Application Number:
  US16/667,071
• Publication Number:
  US 20200131922A1
• Time in Patent Office: 994 Days
• CPC Class Codes: F01D 11/025 Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: F05D 2300/5021 Expansivity
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

Claims

1. A clearance control ring assembly, comprising:

a stator component disposed opposite a rotor component within a gas turbine engine;

a clearance control ring being formed of a single structure and extending circumferentially disposed radially outward of at least a portion of said stator component, said clearance control ring having a coefficient of thermal expansion lower than a coefficient of thermal expansion of said at least a portion of said stator component; and

at least one spring disposed between the stator component and the clearance control ring, the at least one spring configured to provide a radial bias and an axial bias to the clearance control ring;

wherein said at least a portion of said stator component is limited from thermal expansion and limited from growth relative to said rotor component.

2. The clearance control ring assembly of claim 1, wherein said clearance control ring is disposed in a compressor of the gas turbine engine.

3. The clearance control ring assembly of claim 2, wherein said stator component includes a blade ring.

4. The clearance control ring assembly of claim 3, wherein said clearance control ring is disposed outwardly and circumferentially about said blade ring.

5. The clearance control ring assembly of claim 1, further comprising a mid-case ring disposed between a first aft case and a second aft case.

6. The clearance control ring assembly of claim 5, wherein the first aft case and the second aft case each has a flange.

7. The clearance control ring assembly of claim 6, wherein said clearance control ring is disposed between said flanges of the first aft case and the second aft case, respectively.

8. The clearance control ring assembly of claim 6, further comprising a gap between the flange of the first aft case and the flange of the second aft case.

9. The clearance control ring assembly of claim 1, wherein at least one surface of said clearance control ring is angled relative to an axis of said gas turbine engine.

10. The clearance control ring assembly of claim 1, wherein the at least one spring is L-shaped.