Small exit duct for a reverse flow combustor with integrated cooling 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 and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.
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 of the gas turbine engine, the small exit duct including an annular ring removably mounted to the support element and having an outer surface facing the combustion chamber and an opposite inner surface, and a plurality cooling elements integrally formed with the annular ring, the plurality of cooling elements being spaced apart and each extending away from the inner surface, the cooling elements including a plurality of projecting pins and/or ribs, the cooling elements increasing the effective surface area of the inner surface of the annular ring of the small exit duct which is adapted to be cooled by a cooling impingement airflow provided by the gas turbine engine.
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 cooling elements integrally formed with the annular ring to form a monolithic unitary structure of the small exit duct, the plurality of cooling elements being spaced apart and extending away from the inner concave surface of the annular ring, the plurality of cooling elements including a plurality of projecting pins and/or ribs, the cooling elements increasing the effective surface area of the inner concave surface of the annular ring of the small exit duct which is adapted to be cooled by a cooling impingement airflow provided by the gas turbine engine.
A method of forming a reverse flow combustor of a gas turbine engine, the method comprising:
- providing a removable small exit duct having an annular ring and a plurality of cooling elements integrally formed thereon, the plurality of cooling elements being spaced apart and each extending away from an inner surface of the annular ring, the cooling elements including a plurality of projecting pins and/or ribs;
- and
- positioning and removably mounting the small exit duct downstream of an inner liner of the reverse flow combustor on a support element of the gas turbine engine, and disposing the plurality of cooling elements in a path of a cooling impingement airflow provided by the gas turbine engine.
Dependencies are inferred from the claim text.