Passive control of gas turbine clearances using ceramic matrix composites inserts

Patent metadata

Field	Value
Publication number	US-12486780-B2
Application number	US-202519026898-A
Country	US
Kind code	B2
Filing date	Jan 17, 2025
Priority date	Jun 11, 2013
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

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 flow path through the engine core.

First claim

What is claimed is:

1 . A clearance control ring assembly comprising:
an aft case including an angled surface; and a clearance control ring being formed of a single structure, the clearance control ring including an outward portion disposed radially outward of the angled surface and slidably engaging the angled surface, wherein the clearance control ring has a coefficient of thermal expansion lower than a coefficient of thermal expansion of the aft case.

2 . The clearance control ring assembly of claim 1 , wherein the clearance control ring includes an inward portion disposed inward of the angled surface.

3 . The clearance control ring assembly of claim 2 , wherein the inward portion is a blade shroud ring.

4 . The clearance control ring assembly of claim 3 , further comprising a blade including a tip, wherein the blade shroud ring defines a gap with the tip of the blade.

5 . The clearance control ring assembly of claim 4 , wherein the clearance control ring is configured to slide along the angled surface of the aft case during thermal expansion of the clearance control ring assembly to maintain or reduce the gap.

6 . The clearance control ring assembly of claim 2 , wherein the outward portion of the clearance control ring engages the angled surface of the aft case and the inward portion of the clearance control ring engages a surface inward of the angled surface of the aft case.

7 . The clearance control ring assembly of claim 1 , further comprising a second aft case, wherein the outward portion extends from the aft case to the second aft case.

8 . The clearance control ring assembly of claim 7 , wherein the clearance control ring includes an inward portion, wherein the inward portion extends aft from the aft case.

9 . The clearance control ring assembly of claim 7 , further comprising a blade including a tip, wherein the aft case and the second aft case are disposed outward of the tip of the blade.

10 . The clearance control ring assembly of claim 1 , wherein the outward portion has an angled surface that slidably engages the angled surface of the aft case.

11 . The clearance control ring assembly of claim 10 , wherein the angled surface of the outward portion is configured to slide along the angled surface of the aft case during thermal expansion of the clearance control ring assembly.

12 . The clearance control ring assembly of claim 1 , wherein the aft case includes a flat inner surface disposed outward of the angled surface, and wherein the outward portion of the clearance control ring faces the flat inner surface of the aft case.

13 . The clearance control ring assembly of claim 1 , further comprising a forward platform hanger and an aft platform hanger, wherein the clearance control ring extends from the forward platform hanger to the aft platform hanger.

14 . The clearance control ring assembly of claim 13 , wherein one of the forward platform hanger or the aft platform hanger includes a first flange engaged with the aft case.

15 . The clearance control ring assembly of claim 14 , further comprising a second aft case, wherein the other of the forward platform hanger or the aft platform hanger includes a second flange engaged with the second aft case.

16 . The clearance control ring assembly of claim 15 , wherein the clearance control ring includes a blade shroud ring disposed inward of the first flange and the second flange.

17 . The clearance control ring assembly of claim 13 , wherein the angled surface is disposed aft of the forward platform hanger.

18 . A gas turbine engine defining an engine axis, the gas turbine engine comprising:
a compressor; a propulsor; an engine inlet end; a multi-stage high pressure turbine; and the clearance control ring assembly of claim 1 .

19 . The gas turbine engine of claim 18 , wherein the angled surface of the aft case defines a nonzero angle relative to the engine axis.

20 . The gas turbine engine of claim 18 , wherein the clearance control ring assembly further comprises a rotor component, and wherein the clearance control ring and the aft case are disposed outward of the rotor component.

Assignees

• Gen Electric

Inventors

• Mondal Bhaskar Nanda
• Rahaim John Joseph
• Moniz Thomas
• Ross Steven A
• Kirk Joel
• Hunter Scott
• Fusinato Daniel

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2300/5021

  Expansivity · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2240/55

  Seals · CPC title