Control rings

Patent metadata

Field	Value
Publication number	US-10612408-B2
Application number	US-201514705273-A
Country	US
Kind code	B2
Filing date	May 6, 2015
Priority date	May 6, 2015
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.

First claim

What is claimed is:

1. A control ring for use in a gas turbine engine, the control ring comprising:
a ring shape defining a centerline axis, wherein the control ring includes an inner diameter surface and an outer diameter surface, wherein the inner diameter surface and the outer diameter surface extend in a circumferential direction, the control ring is configured for being supported in a control ring carrier that is disposed between a blade outer air seal and an external case; and
a plurality of thermally isolating contacts that are circumferentially spaced along the control ring, operatively connected to at least one of the inner diameter surface and the outer diameter surface, wherein the thermally isolating contacts have lower thermal conductivity than the control ring,
wherein each of the plurality of thermally isolating contacts is block shaped or cylindrical shaped and extends from a respective one of a plurality of cavities in the control ring, wherein the respective one of the plurality of cavities has a same shape as the respective one of the thermally isolating contacts, wherein each of the thermally isolating contacts extends exterior to the control ring and is configured to engage the control ring carrier to thereby support and thermally isolate the control ring within the control ring carrier; and
the plurality of thermally isolating contacts extend radially outward from within the at least one of the inner diameter surface and the outer diameter surface.

2. A control ring as recited in claim 1 , wherein the control ring comprises a plurality of control ring segments that are circumferentially joined together to form the control ring configured to be held in the control ring carrier for thermal isolation from the blade outer air seal.

3. A control ring as recited in claim 1 , wherein one or more of the plurality of thermally isolating contacts extends from a respective one or more of the cavities on the outer diameter surface of the control ring segment, wherein the thermally isolating contacts are circumferentially spaced apart from one another.

4. A control ring as recited in claim 1 , wherein one or more of the thermally isolating contacts extends from a respective one or more of the cavities on the inner diameter surface of the control ring segment.

5. A control ring as recited in claim 1 , wherein the plurality of thermally isolating contacts are a plurality of thermally isolating inlays that are inlayed into the respective plurality of cavities in the control ring.

6. A control ring as recited in claim 5 , wherein the control ring includes a plurality of the cavities on the inner diameter surface with a respective plurality of the thermally isolating inlays defined therein, wherein the plurality of thermally isolating inlays extending to the inner diameter surface and defining the thermally isolating contacts.

Assignees

• United Technologies Corp

Inventors

• Borja Mark

Classifications

• F05D2300/5024

  Heat conductivity · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F16J15/442

  segmented · CPC title

• F01D11/18 Primary

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

• F05D2300/5023

  Thermal capacity · CPC title