Use of high temperature insulation for ceramic matrix composites in gas turbines
Abstract
A ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere and the arrangement of spheres is such that the composition is dimensionally stable and chemically stable at a temperature of approximately 1600.degree. C. A stationary vane of a gas turbine comprising the composition of the present invention bonded to the outer surface of the vane is provided. A combustor comprising the composition bonded to the inner surface of the combustor is provided. A transition duct comprising the insulating coating bonded to the inner surface of the transition is provided. Because of abradable properties of the composition, a gas turbine blade tip seal comprising the composition also is provided. The composition is bonded to the inside surface of a shroud so that a blade tip carves grooves in the composition so as to createmore »
- Inventors:
-
- Orlando, FL
- Pittsburgh, PA
- New Boston, NH
- Murrysville, PA
- Issue Date:
- Research Org.:
- Westinghouse Electric Corp., Pittsburgh, PA (United States)
- OSTI Identifier:
- 873588
- Patent Number(s):
- 6197424
- Assignee:
- Siemens Westinghouse Power Corporation (Orlando, FL)
- Patent Classifications (CPCs):
-
C - CHEMISTRY C04 - CEMENTS C04B - LIME, MAGNESIA
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- DOE Contract Number:
- FC21-95MC32267
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- temperature; insulation; ceramic; matrix; composites; gas; turbines; composition; insulating; components; provided; comprises; plurality; hollow; oxide-based; spheres; various; dimensions; phosphate; binder; oxide; filler; powder; whereby; partially; fills; gaps; powders; situated; sphere; contact; arrangement; dimensionally; stable; chemically; approximately; 1600; degree; stationary; vane; turbine; comprising; bonded; outer; surface; combustor; inner; transition; duct; coating; abradable; properties; blade; tip; seal; inside; shroud; carves; grooves; create; customized; filler powders; ceramic matrix; matrix composites; composition comprises; ceramic composition; inside surface; turbine blade; gas turbine; inner surface; outer surface; gas turbines; dimensionally stable; blade tip; phosphate binder; matrix composite; binder partially; oxide-based spheres; partially fills; oxide filler; coating bonded; filler powder; temperature insulation; insulating coating; seal comprising; combustor comprising; fills gaps; tip seal; hollow oxide-based; chemically stable; stationary vane; /428/416/
Citation Formats
Morrison, Jay Alan, Merrill, Gary Brian, Ludeman, Evan McNeil, and Lane, Jay Edgar. Use of high temperature insulation for ceramic matrix composites in gas turbines. United States: N. p., 2001.
Web.
Morrison, Jay Alan, Merrill, Gary Brian, Ludeman, Evan McNeil, & Lane, Jay Edgar. Use of high temperature insulation for ceramic matrix composites in gas turbines. United States.
Morrison, Jay Alan, Merrill, Gary Brian, Ludeman, Evan McNeil, and Lane, Jay Edgar. Mon .
"Use of high temperature insulation for ceramic matrix composites in gas turbines". United States. https://www.osti.gov/servlets/purl/873588.
@article{osti_873588,
title = {Use of high temperature insulation for ceramic matrix composites in gas turbines},
author = {Morrison, Jay Alan and Merrill, Gary Brian and Ludeman, Evan McNeil and Lane, Jay Edgar},
abstractNote = {A ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere and the arrangement of spheres is such that the composition is dimensionally stable and chemically stable at a temperature of approximately 1600.degree. C. A stationary vane of a gas turbine comprising the composition of the present invention bonded to the outer surface of the vane is provided. A combustor comprising the composition bonded to the inner surface of the combustor is provided. A transition duct comprising the insulating coating bonded to the inner surface of the transition is provided. Because of abradable properties of the composition, a gas turbine blade tip seal comprising the composition also is provided. The composition is bonded to the inside surface of a shroud so that a blade tip carves grooves in the composition so as to create a customized seal for the turbine blade tip.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Mon Jan 01 00:00:00 EST 2001},
month = {Mon Jan 01 00:00:00 EST 2001}
}