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Title: Thermal shields for gas turbine rotor

A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
Inventors:
;
Issue Date:
OSTI Identifier:
1399249
Assignee:
SIEMENS ENERGY, INC. NETL
Patent Number(s):
9,771,802
Application Number:
14/189,147
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2014 Feb 25
Research Org:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Other works cited in this record:

Free standing turbine disk sideplate assembly
patent, May 1994

Turbines with platforms between stages
patent, March 1997

Arrangement for the thermal protection of a rotor of a high-pressure compressor
patent, December 1998

Heat shield device in gas turbines
patent, July 2002

Rotor with core surrounded by shielding rings
patent, January 2009

Compressor rotor
patent, October 2011

Device and system for reducing secondary air flow in a gas turbine
patent-application, July 2010

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