Small exit duct for a reverse flow combustor with integrated fastening elements
AssigneePratt & Whitney Canada Corp.
InventorsHONZA STASTNY, ROBERT SZE
Life of this patent
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Abstract
The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.
Claims20
A reverse flow combustor of a gas turbine engine comprising:
- inner and outer combustor liners defining a combustor chamber therewithin;
- a large exit duct disposed at a downstream end of the outer liner forming a continuation of the outer liner;
- and
- a small exit duct disposed at and communicating with a downstream end of the inner liner, the small exit duct and the large exit duct cooperating to define a reverse flow exit passage therebetween that is configured to communicate with a turbine section of the gas turbine;
- wherein the small exit duct is removably fastened to a support element, the small exit duct including an annular ring having an outer surface facing the combustion chamber and extending downstream from the inner combustor liner, the annular ring being removably mounted to the support element of the gas turbine engine by one or more fastening elements integrally formed with the annular ring, the fastening elements being mountable with corresponding features of the support element and removably fastened thereto.
A small exit duct for a reverse flow combustor of a gas turbine engine, the small exit duct comprising an annular ring having an arcuate cross-section and defining an outer convex surface and an opposite inner concave surface, and a plurality of mounting studs extending from the inner concave surface of the annular ring, the mounting studs being integrally formed with the annular ring to form a monolithic unitary structure of the small exit duct, the mounting studs being configured to be removably fastened to corresponding features of a support element, the small exit duct being thereby removably mountable in place within the reverse flow combustor.
A method of forming a reverse flow combustor of a gas turbine engine, the method comprising:
- providing a small exit duct having an annular ring and one or more fastening elements integrally formed thereon;
- and
- positioning the small exit duct downstream of an inner liner of the reverse flow combustor such that an outer surface of the annular ring faces a combustion chamber of the reverse flow combustor, and removably fastening the small exit duct in place by mating the fastening elements of the small exit duct with corresponding features in a support element of the reverse flow combustor.
A method of repairing a reverse flow combustor of a gas turbine engine having a large exit duct and a small exit duct respectively disposed at downstream ends of outer and inner combustor liners, the method comprising:
- detaching one or more fastening elements removably connecting the small exit duct to an associated support element;
- removing the small exit duct from a remainder of the reverse flow combustor without damaging or removing at least the large exit duct;
- and
- replacing the removed small exit duct by a new small exit duct, by position the new small exit duct in place within the reverse flow combustor and fastening said new small exit duct to said associated support element using fastening elements integrally formed with the new small exit duct.
Dependencies are inferred from the claim text.