US 6,397,603 B1Granted

Conbustor having a ceramic matrix composite liner

AssigneeThe United States of America as represented by the Secretary of the Air Force

InventorsWayne Garcia Edmondson, James Dale Steibel, Harold Ray Hansel

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Abstract

A combustor having liners made from ceramic matrix composite materials (CMC's) that are capable of withstanding higher temperatures than metallic liners. The ceramic matrix composite liners are used in conjunction with mating components that are manufactured from superalloy materials. To permit the use of a combustor having liners made from CMC materials in conjunction with metallic materials used for the mating forward cowls, and aft seals with attached seal retainer over the broad range of temperatures of a combustor, the combustor is designed to allow for the differential thermal expansion of the differing materials at their interfaces in a manner that does not introduce stresses into the liner as a result of thermal expansion and also balances the flow of cooling air as a result of the thermal expansion.

Claims22

Dependent claims

A combustor for use in a gas turbine engine, comprised of:

a forward cowl made from a metallic material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere having a first coefficient of thermal expansion;
an aft seal attached to a seal retainer, the aft seal having a second coefficient of thermal expansion and the seal retainer having a third coefficient of thermal expansion, each made from a metallic material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere;
and
a combustion liner made from a ceramic matrix composite material capable of withstanding elevated temperatures of combustion in an oxidative and corrosive atmosphere having a fourth coefficient of thermal expansion less than the first coefficient of thermal of the forward cowl and less than the second coefficient of thermal expansion of the aft seal and less than the third coefficient of thermal expansion of the seal retainer, the combustor liner positioned between the forward cowl and aft seal with attached seal retainer in a manner to permit differential thermal expansion of the ceramic combustor liner, the forward cowl and the aft seal with attached seal retainer without introducing stresses into the liner sufficient to fracture the liner as a result of differential thermal expansion at elevated temperatures.

1 more element

A combustor for use in a gas turbine engine, comprised of:

at least one metallic forward cowl at a fore end of the combustor;
a metallic inner dome support including an inner liner support attached to the at least one forward cowl, the inner liner support including an expansion aperture;
a metallic outer dome support including an outer liner support attached to the at least one forward cowl, the outer liner support including an expansion aperture;
a fuel nozzle swirler attached to the a dome supports to mix fuel and air to initiate combustion of fuel and direct hot gases of combustion into a combustion chamber and then into a turbine portion of the gas turbine engine;
at least one metallic aft seal at the aft end of the combustor;
a metallic aft seal retainer attached to the aft seal so that a gap is created between the aft seal and the at least one aft seal retainer;
a ceramic inner combustion liner forming the inner wall of the combustor chamber and having a forward attachment and an aft attachment in the form of a flange extending away from a centerline of the combustor, the liner extending between the inner dome support and the at least one aft seal, the forward attachment of the combustion liner assembled into the expansion aperture in the inner liner support, and the aft attachment fitting into the gap between the aft seal and the at least one aft seal retainer;
a ceramic outer combustion liner forming an outer wall of the combustor chamber and having a forward attachment and an aft attachment in the form of a flange extending away from a centerline of the combustor, the liner extending between the outer dome support and the at least one aft seal, the forward attachment of the combustion liner assembled into the expansion aperture of the liner support, and the aft attachment fitting into the gap between the aft seal and the at least one aft seal retainer;
and
means for attaching the combustor liners to the liner supports.

7 more elements

Dependencies are inferred from the claim text.

Facts

Application: 09/567,557Filed 5 May 2000
Granted: 4 Jun 2002
Term ends: Not estimatedThe source records don’t support an estimate.

Classification7 codes

F23R 3/007
Continuous combustion chambers using liquid or gaseous fuel: constructed mainly of ceramic components
F23R 3/60
Characterised by the arrangement or form of the flame tubes or combustion chambers: support structures; Attaching or mounting means
F05B 2230/606
Using positioning or alignment devices for aligning or centering, e.g. pins: using maintaining alignment while permitting differential dilatation
F23D 2212/103
Ceramic: fibres