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    BLADE FOR A TURBOMACHINE TURBINE, COMPRISING INTERNAL PASSAGES FOR CIRCULATING COOLING AIR
    2.
    发明申请
    BLADE FOR A TURBOMACHINE TURBINE, COMPRISING INTERNAL PASSAGES FOR CIRCULATING COOLING AIR 审中-公开

    公开(公告)号：US20200173290A1

    公开(公告)日：2020-06-04

    申请号：US16615328

    申请日：2018-05-18

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Leandre OSTINO ,  Patrice ENEAU ,  Charlotte Marie DUJOL

    IPC: F01D5/18 ,  F02C7/18

    Abstract: In order to limit the air flow required to cool its blade member, a blade for an aircraft turbomachine turbine includes, in its blade member, a main passage configured to collect a main air flow from an air inlet and to circulate it in the blade member, and a side passage located between the main passage and the pressure-side wall, while being separated from the main passage, wherein the side passage is configured to collect a side air flow from the air inlet and to circulate it in the blade member, the main passage having at least three portions connected together end-to-end to form a coil, the side passage being located between each of these portions and the pressure-side wall.

    Aircraft Turbomachine Blade and Method for Manufacturing Same Using Lost-Wax Casting
    4.
    发明申请
    Aircraft Turbomachine Blade and Method for Manufacturing Same Using Lost-Wax Casting 有权

    公开(公告)号：US20220170371A1

    公开(公告)日：2022-06-02

    申请号：US17440853

    申请日：2020-03-11

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Michel SLUSARZ ,  Pierre Guillaume AUZILLON ,  Patrice ENEAU ,  Léandre OSTINO

    IPC: F01D5/14

    Abstract: An aircraft turbine engine blade includes at least one inner cavity for circulating a ventilation air flow and having a wall with first projecting elements oriented in a first direction and forming air flow disrupters, and at least a second projecting element oriented in a second direction different from the first direction. The second projecting element and at least one of the first projecting elements overlap each other in one area. At least one of the first projecting elements overlaps the second projecting element and has a height (H2, H4′) which is greater than that of the second projecting element in the area and greater than that of the other first projecting elements of the wall, in order to retain its disruptive function along the entire length thereof.

    BLADE PROVIDED WITH A COOLING CIRCUIT
    6.
    发明申请
    BLADE PROVIDED WITH A COOLING CIRCUIT 有权

    公开(公告)号：US20220268160A1

    公开(公告)日：2022-08-25

    申请号：US17629482

    申请日：2020-07-24

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Michel SLUSARZ ,  Patrice ENEAU ,  Charlotte Marie DUJOL

    IPC: F01D5/18

    Abstract: A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade, wherein at least one ventilation cavity is a ventilation cavity of a first type comprising at least one ascending portion which extends substantially longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and at least one discharge portion which extends substantially transversely and which opens at the trailing edge via at least one port of the trailing edge, and wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends substantially longitudinally from the apex, engaged with the upper surface wall and spaced from the lower

    TURBINE BLADE WITH OPTIMISED COOLING AT THE TRAILING EDGE OF SAME COMPRISING UPSTREAM AND DOWNSTREAM DUCTS AND INNER SIDE CAVITIES
    8.
    发明申请
    TURBINE BLADE WITH OPTIMISED COOLING AT THE TRAILING EDGE OF SAME COMPRISING UPSTREAM AND DOWNSTREAM DUCTS AND INNER SIDE CAVITIES 审中-公开

    公开(公告)号：US20170191368A1

    公开(公告)日：2017-07-06

    申请号：US15314037

    申请日：2015-05-26

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Charlotte Marie DUJOL ,  Patrice ENEAU

    IPC: F01D9/04 ,  F01D9/06

    Abstract: A turbine blade including a root, a vane extending in a spanwise direction, ending at a tip and including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, the vane further including at least one upstream duct configured to collect air at the root to cool the leading edge, discharging the air through holes passing through the wall of the leading edge; at least one downstream duct separate from the upstream duct and configured to collect air at the root to cool the trailing edge, discharging the air through holes passing through the pressure wall upstream from the trailing edge; an inner side cavity running along the pressure-side wall to form a heat shield insulating the downstream duct.

    TURBOMACHINE MOVING BLADE WITH COOLING CIRCUIT HAVING A DOUBLE ROW OF DISCHARGE SLOTS
    9.
    发明申请
    TURBOMACHINE MOVING BLADE WITH COOLING CIRCUIT HAVING A DOUBLE ROW OF DISCHARGE SLOTS 有权

    公开(公告)号：US20220316344A1

    公开(公告)日：2022-10-06

    申请号：US17597549

    申请日：2020-07-22

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Patrice ENEAU ,  Michel SLUSARZ

    IPC: F01D5/18 ,  F01D5/30

    Abstract: The invention relates to a movable turbomachine blade comprising at least one cooling circuit comprising at least one cavity extending radially between the root and the tip, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots arranged to open out along the trailing edge between the root and the tip, and a plurality of second discharge slots separate from the first discharge slots and arranged along the trailing edge between the root and the tip, the second discharge slots being offset axially upstream relative to the first discharge slots and each of the first discharge slots being radially offset relative to each of the second discharge slots, with no overlap between the first and second discharge slots.

    BLADE COMPRISING A TRAILING EDGE HAVING THREE DISTINCT COOLING REGIONS
    10.
    发明申请
    BLADE COMPRISING A TRAILING EDGE HAVING THREE DISTINCT COOLING REGIONS 审中-公开

    公开(公告)号：US20180306035A1

    公开(公告)日：2018-10-25

    申请号：US15765334

    申请日：2016-10-04

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Patrice ENEAU ,  Sebastien Serge Francis CONGRATEL ,  Charlotte Marie DUJOL ,  Philippe PICOT

    IPC: F01D5/18 ,  B22C9/10

    Abstract: A turbine blade including a root bearing an aerofoil extending in a direction of span and ending in a tip, this aerofoil including a leading edge and a trailing edge which are connected by a pressure face wall and a suction face wall, the trailing edge including on the pressure face side cooling slots. The trailing edge includes one or more first slots close to the root, which are supplied via a lower cavity; one or more last slots near the tip which are supplied via an upper cavity; intermediate slots situated between the first slots and the last slots supplied with air via a downstream line set; and wherein the lower cavities and upper cavities and the downstream line set are supplied distinctly at the level of the root.

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