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Title: Ceramic gas turbine shroud

Abstract

An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed.

Inventors:
;
Publication Date:
Research Org.:
Hamilton Sundstrand Corporation, Windsor Locks, CT (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1149909
Patent Number(s):
8,784,052
Application Number:
12/776,673
Assignee:
Hamilton Sundstrand Corporation (Windsor Locks, CT) NETL
DOE Contract Number:
FC26-00CH11060
Resource Type:
Patent
Resource Relation:
Patent File Date: 2010 May 10
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Shi, Jun, and Green, Kevin E. Ceramic gas turbine shroud. United States: N. p., 2014. Web.
Shi, Jun, & Green, Kevin E. Ceramic gas turbine shroud. United States.
Shi, Jun, and Green, Kevin E. Tue . "Ceramic gas turbine shroud". United States. doi:. https://www.osti.gov/servlets/purl/1149909.
@article{osti_1149909,
title = {Ceramic gas turbine shroud},
author = {Shi, Jun and Green, Kevin E.},
abstractNote = {An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jul 22 00:00:00 EDT 2014},
month = {Tue Jul 22 00:00:00 EDT 2014}
}

Patent:

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  • A support system for supporting the stationary ceramic vanes and ceramic outer shrouds which define the motive fluid gas path in a gas turbine engine is shown. Each individual segment of the ceramic component whether a vane or shroud segment has an integral radially outwardly projecting stem portion. The stem is enclosed in a split collet member of a high-temperature alloy material having a cavity configured to interlock with the stem portion. The generally cylindrical external surface of the collet engages a mating internal cylindrical surface of an aperture through a supporting arcuate ring segment with mating camming surfaces onmore » the two facing cylindrical surfaces such that radially outward movement of the collet relative to the ring causes the internal cavity of the collet to be reduced in diameter to tightly engage the ceramic stem disposed therein. A portion of the collet extends outwardly through the ring segment opposite the ceramic piece and is threaded for receiving a nut and a compression washer for retaining the collet in the ring segment under a continuous biasing force urging the collet radially outwardly.« less
  • The back side recessed cooling surface of a shroud defining in part the hot gas path of a turbine is electrochemically machined to provide surface roughness elements and spaces therebetween to increase the heat transfer coefficient. To accomplish this, an electrode with insulating dielectric portions and non-insulating portions is disposed in opposition to the cooling surface. By passing an electrolyte between the cooling surface and electrode and applying an electrical current between the electrode and a shroud, roughness elements and spaces therebetween are formed in the cooling surface in opposition to the insulating and non-insulating portions of the electrode, hencemore » increasing the surface area and heat transfer coefficient of the shroud.« less
  • An open cooling circuit for a gas turbine bucket wherein the bucket has an airfoil portion, and a tip shroud, the cooling circuit including a plurality of radial cooling holes extending through the airfoil portion and communicating with an enlarged internal area within the tip shroud before exiting the tip shroud such that a cooling medium used to cool the airfoil portion is subsequently used to cool the tip shroud.
  • An open cooling circuit for a gas turbine airfoil and associated tip shroud includes a first group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a leading edge of the airfoil; a second group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a trailing edge of the airfoil. A common plenum is formed in the tip shroud in direct communication with the first and second group of cooling holes, but a second plenum may be provided for the second group of radial holes. Amore » plurality of exhaust holes extends from the plenum(s), through the tip shroud and opening along a peripheral edge of the tip shroud.« less
  • This patent describes improvement in a gas turbine engine of the type having a core engine, a shroud surrounding the core engine, a tubular outer nacelle defining an annular bypass duct therebetween and a fan disposed in the nacelle inlet for directing compressed gas flow into and through the bypass duct, the shroud formed in two axially divided halves, each having a generally C shaped center cross section with radially extending flanges secured to the axial edges of the center section. The improvement comprises: each shroud comprises an integral panel having a honeycomb core and continuous facesheets bonded to bothmore » surfaces, wherein corner regions between the center section and the flanges are comprised of a honeycomb core having a higher density than the honeycomb core in the center section and flanges.« less