AIRCRAFT TURBOMACHINE
The turbomachine's innovative configuration positions the combustion chamber and fuel supply system outside the burst zone, using a heat exchanger to reduce combustible gas volume and energy needs, addressing safety and efficiency challenges with combustible gases like dihydrogen.
FR3155029B1Active Publication Date: 2025-09-26SAFRAN AIRCRAFT ENGINES SAS
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Patent Information
- Application Number
- FR2023011978
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2023-11-03
- Publication Date
- 2025-09-26
- Estimated Expiration
- 2043-11-03
Abstract
The invention relates to a turbomachine (4) comprising: - a low-pressure body (8), - a high-pressure body (9), - an annular combustion chamber (25), and the turbomachine (4) being characterized in that: - the high-pressure turbine (16) is located at the rear of the low-pressure body (8), and, - the combustion chamber (25) is located at the rear of the low-pressure and high-pressure bodies (8, 9), and in that it further comprises: - a first heat exchanger (27) located in the primary flow path (v1) between the low-pressure turbine (11) and the high-pressure turbine (16), the first heat exchanger (27) comprising a first circuit for passing air from the high-pressure compressor (15) and supplying the combustion chamber (25), and a second circuit for passing gases from the combustion chamber (25). Abstract figure: figure 2
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