MODULE FOR AN AIRCRAFT TURBOMACHINE

FR3166165A1Pending Publication Date: 2026-03-13SAFRAN AIRCRAFT ENGINES SAS
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Patent Information

Authority / Receiving Office
FR · FR
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-09-06
Publication Date
2026-03-13
Patent Text Reader

Abstract

Module (10) for an aircraft turbomachine, this module (10) comprising: - a rotor including a centrifugal compressor impeller (12) and a turbine impeller (16) (22), - a stator-diffuser (26) mounted at the outlet of the impeller (20), - a turbine distributor (28) mounted upstream of the impeller (22), - an annular combustion chamber (14) axially interposed between the stator-diffuser (26) and the distributor (28), - a vent air injector (56) surrounded by the combustion chamber (14), and - a lamination (32) connecting the stator-diffuser (26) to the distributor (28) and to the injector (56), this lamination (32) being configured to provide a purge air flow to the turbine. Figure for the abbreviation: Figure 1
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Citation Information

Patent Citations

  • Cooling system for a downstream cavity of a centrifugal compressor impeller

    FR2904034A1

  • Centrifugal compressor impeller downstream face cooling system for aircraft turbomachine e.g. turbojet and jet prop engines, has cylindrical passage and sheet guiding drawn ventilating air till neighborhood of downstream face of impeller

    FR2904038A1

  • VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE

    FR2937371A1

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  • Lower cavity ventilation system for e.g. jet engine, has flux deflection unit with sheets fixedly mounted in cavity of wheel for guiding ventilation air radially from interior towards exterior along lower face of wheel

    FR2904036A1