Recovered-cycle aircraft turbine engine
AssigneeSafran Helicopter Engines
InventorsAlexandre AUDUBERTEAU, Lionel SCUILLER, Alphonse PUERTO
Life of this patent
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Abstract
An aircraft turbine engine having a compressor,—an annular combustion chamber, a system for diffusing and straightening an air stream exiting the compressor in order to supply the combustion chamber, and a heat exchanger, this heat exchanger having: a first circuit supplied with exhaust gas from the turbine engine, and a second circuit comprising an inlet (38ba) connected by a first scroll to an outlet of the diffuser, and an outlet connected by a second scroll to an inlet of the straightener, the scrolls including connecting arms that rigidly connect the annular portions of the scrolls which are secured or connected to the diffuser and to the straightener, respectively.
Claims13
An aircraft turbine engine, comprising:
- a compressor extending around an axis,
- an annular combustion chamber extending around the axis A,
- a system for diffusing and straightening an air stream exiting the compressor to supply the combustion chamber, this system comprising:
- an annular diffuser comprising a substantially radially oriented outlet and an inlet supplied by the compressor, and
- an annular straightener which comprises an outlet (36b) for supplying the combustion chamber, and
- a heat exchanger this exchanger comprising:
- + a first circuit supplied with exhaust gas from the turbine engine, and
- + a second circuit comprising an inlet (38ba) connected by a first volute to the outlet of the diffuser, and an outlet connected by a second volute to an inlet of the straightener, the first and second volutes being placed side by side and each comprising an annular duct wound around the axis and connected to a first port located at the external periphery of the duct and oriented in the tangential direction, and a second port located at the internal periphery of the duct and defining an annular vein of air passage,
- wherein the second port of each of the first and second volutes comprises connecting arms distributed around the axis, these connecting arms extending axially and/or radially through the vein of the second port and rigidly connecting annular portions of the first and second volutes which are attached or connected respectively to the diffuser and to the straightener.
Dependencies are inferred from the claim text.