Gas turbine engine
AssigneeROLLS-ROYCE plc
InventorRichard G. Stretton
Life of this patent
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Abstract
A heat exchanger arrangement for a gas turbine engine. The arrangement including a flow path within an outer cowl, which flow path locates a heat exchanger part way therealong. A valve is provided at an inlet end of the flow path to selectively receive fluid into the flow path from outside of the cowl and/or from a pressurized fluid flow. An exit from the flow path includes a plenum chamber to receive exhausted coolant flows from the heat exchanger and possibly other exhaust flows. The heat exchanger exhaust flow is then utilized to provide cooling to engine structures.
Claims19
A gas turbine engine comprising a compressor driven by a turbine, with a combustor located between the compressor and the turbine, a main propulsive rotor is provided downstream of the combustor which rotor is driven by a second turbine,
- the engine also comprising a heat exchanger arrangement,
- the heat exchanger arrangement comprising a flow path within an outer cowl,
- a heat exchanger at an intermediate position along the flow path between an inlet and an outlet,
- the flow path arranged about a pressurized fluid flow through the engine,
- the inlet has a valve selectively movable between a first position to receive into the flow path fluid from outside of the engine, and a second position to receive into the flow path fluid from the pressurized fluid flow, and that the outlet has a plenum chamber associated with the pressurized fluid flow.
An engine as claimed in 7 wherein the valve can be selectively configured to receive into the flow path fluid from both outside of the cowl and from the pressurized fluid flow.
Dependencies are inferred from the claim text.