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公开(公告)号：US11988385B2
公开(公告)日：2024-05-21
申请号：US18002011
申请日：2021-06-09
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Jean-Paul Didier Autret , Thomas Sebastien Alexandre Gresy , Stéphane Lavignotte , Nicolas Roland Guy Savary
CPC classification number: F23R3/002 , F23R3/005 , B33Y80/00 , F23R2900/00018 , F23R2900/03042
Abstract: A gas turbomachine combustion chamber includes bridges extending side by side to connect in one piece a radially inner wall and a radially outer wall towards a free end of the radially inner wall. The bridges, inner wall, and outer wall have an additive layer structure.
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公开(公告)号：US20240044492A1
公开(公告)日：2024-02-08
申请号：US18258356
申请日：2021-12-20
Applicant: SAFRAN HELICOPTER ENGINES
IPC: F23R3/00
CPC classification number: F23R3/005 , F23R3/002 , F23R2900/03043
Abstract: A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams outside the external wall, which cool the internal wall. The internal wall being free of perforations prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.
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公开(公告)号：US12078351B2
公开(公告)日：2024-09-03
申请号：US18258356
申请日：2021-12-20
Applicant: SAFRAN HELICOPTER ENGINES
IPC: F23R3/00
CPC classification number: F23R3/005 , F23R3/002 , F23R2900/03043
Abstract: A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams, outside the external wall, which cool the internal wall. The internal wall being free of perforations to prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.
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公开(公告)号：US20220252268A1
公开(公告)日：2022-08-11
申请号：US17616280
申请日：2020-06-03
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Stéphane Lavignotte , Guillaume Thierry Cottin , Jean-Paul Didier Autret , Mehdi Deliba , Thomas Sebastien Alexandre Gresy , Nicolas Roland Guy Savary
IPC: F23R3/44 , B23K26/342 , B22F10/28 , B33Y10/00
Abstract: A method for manufacturing a flame tube for a turbomachine, the flame tube extending about an axis and comprising an annular radially internal wall and an annular radially external wall, connected to each other by an end wall or head wall, the internal wall, the external wall and the end wall defining an internal volume, at least one part of the said end wall forming a double wall comprising a first part and a second part connected to each other and spaced apart from each other so as to delimit a flow channel for a flow of cooling air opening into the said internal volume, the said flow channel comprising at least one air-inlet opening, the first and second parts of the double wall being connected by connecting zones or bridges extending into the flow channel for the cooling-air flow, the flame tube being manufactured by additive manufacturing.
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