초록

A method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct.

대표청구항 ▼

We claim: 1. A cooling apparatus for cooling a fluid in a bypass duct of a gas turbine engine, the apparatus comprising a heat exchanger mounted entirely inside an annular portion of the bypass duct, the heat exchanger mounted to only one annular peripheral wall defining an annular periphery of the

We claim: 1. A cooling apparatus for cooling a fluid in a bypass duct of a gas turbine engine, the apparatus comprising a heat exchanger mounted entirely inside an annular portion of the bypass duct, the heat exchanger mounted to only one annular peripheral wall defining an annular periphery of the annular portion of the bypass duct, the heat exchanger mounted so that only an external peripheral surface of the heat exchanger is directly exposed to an airflow through the bypass duct, the heat exchanger co-operating with the peripheral wall to define therebetween a fluid passageway extending substantially parallel to the annular wall, the fluid passageway being in fluid communication with a source of liquid to be cooled. 2. The cooling apparatus as claimed in claim 1 wherein the heat exchanger member is a piece of sheet metal mounted to the outer annular wall of the bypass duct. 3. The cooling apparatus as claimed in claim 2 wherein the piece of sheet metal comprises a depressed portion at least partially defining the fluid passageway. 4. A gas turbine engine comprising: an annular bypass duct adapted to direct bypass air through the engine; and a fluid passageway provided adjacent the bypass duct and extending substantially parallel to an annular peripheral wall defining the duct, the fluid passageway being in fluid communication with an oil system of the gas turbine engine, the fluid passageway directly exposed with the air passing through the bypass duct, the fluid passageway defined by only one outer annular peripheral wall defining the duct cooperating with a piece of sheet metal with a depressed portion mounted to said one peripheral wall. 5. The gas turbine engine as claimed in claim 4, wherein said fluid passageway is provided on an outer surface of said outer annular peripheral wall of the bypass duct.