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    VARIABLE THERMAL INSULATION
    21.
    发明公开
    VARIABLE THERMAL INSULATION 审中-公开

    公开(公告)号：US20240280209A1

    公开(公告)日：2024-08-22

    申请号：US18111092

    申请日：2023-02-17

    Applicant: Collins Engine Nozzles, Inc.

    Inventor： Jason A. Ryon ,  Viktor Kilchyk ,  Eric Surawski

    IPC: F16L59/06 ,  B64G1/58 ,  F16L59/065 ,  F16L59/07

    CPC classification number: F16L59/06 ,  B64G1/58 ,  F16L59/065 ,  F16L59/07 ,  F28F2013/008

    Abstract: A system includes a wall panel with an exterior wall. An interior wall is separated from the interior wall by a variable insulation gap occupied by an insulation medium. A flow driver is connected in fluid communication with the insulation medium. The flow driver is configured to selectively switch properties of the insulation medium in the variable insulation gap between a conduction mode and in an insulation mode. The insulation medium has a first effective thermal conductivity in the insulation mode, and a second effective thermal conductivity in the conduction mode. The first effective thermal conductively is lower than the second effective thermal conductivity.

    COMBUSTOR SECTION SUPPORT STRUCTURES
    22.
    发明公开
    COMBUSTOR SECTION SUPPORT STRUCTURES 审中-公开

    公开(公告)号：US20240271794A1

    公开(公告)日：2024-08-15

    申请号：US18141328

    申请日：2023-04-28

    Applicant: Collins Engine Nozzles, Inc.

    Inventor： Kevin Thompson ,  Jason A. Ryon

    IPC: F23R3/60 ,  F02C7/22

    CPC classification number: F23R3/60 ,  F02C7/222

    Abstract: A combustor section support structure can include a fuel manifold and one or more radial stud assemblies connected to the fuel manifold and configured to allow the fuel manifold to move radially relative to an engine case and to fix the fuel manifold axially relative to the engine case. Each of the one or more radial stud assemblies can include a first portion mounted to the fuel manifold and a second portion configured to mount to an engine case. The first portion and the second portion can be configured to slide relative to each other to allow relative radial movement, but to prevent substantial axial relative movement. The first portion and the second portion form a ball joint assembly configured to allow misalignment induced rotation at the ball joint assembly.

    COMBUSTOR SECTION SUPPORT STRUCTURES
    23.
    发明公开
    COMBUSTOR SECTION SUPPORT STRUCTURES 审中-公开

    公开(公告)号：US20240271788A1

    公开(公告)日：2024-08-15

    申请号：US18109804

    申请日：2023-02-14

    Applicant: Collins Engine Nozzles, Inc.

    Inventor： Jason A. Ryon ,  Brandon P. Williams

    IPC: F23R3/28 ,  F23R3/60

    CPC classification number: F23R3/28 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00012 ,  F23R2900/00017

    Abstract: A combustor section support structure can include a fuel manifold and one or more radial stud assemblies connected to the fuel manifold and configured to allow the fuel manifold to move radially relative to an engine case and to fix the fuel manifold axially relative to the engine case. Each of the one or more radial stud assemblies can include a first portion mounted to the fuel manifold and a second portion configured to mount to an engine case. The first portion and the second portion can be configured to slide relative to each other to allow relative radial movement, but to prevent axial relative movement. A system can include a fuel manifold configured to distribute fuel to one or more fuel nozzles of a turbomachine, and a fuel inlet assembly configured to connect to the fuel manifold through an engine case. The fuel inlet assembly can be configured to axially retain the fuel manifold relative to the engine case and to allow radial movement of the fuel manifold relative to the engine case.

    TORCH IGNITORS WITH GAS ASSIST START
    26.
    发明公开
    TORCH IGNITORS WITH GAS ASSIST START 审中-公开

    公开(公告)号：US20230323811A1

    公开(公告)日：2023-10-12

    申请号：US18210139

    申请日：2023-06-15

    Applicant: Collins Engine Nozzles, Inc.

    Inventor： Jason A. Ryon ,  Brandon Phillip Williams

    IPC: F02C7/04 ,  F02C3/00 ,  F23R3/00 ,  F23R3/34 ,  F02C7/264

    CPC classification number: F02C7/04 ,  F02C3/00 ,  F23R3/002 ,  F23R2900/03343 ,  F02C7/264 ,  F05D2220/32 ,  F23R3/343

    Abstract: An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.

    SWIRL VALVES
    29.
    发明申请
    SWIRL VALVES 有权

    公开(公告)号：US20250092831A1

    公开(公告)日：2025-03-20

    申请号：US18370502

    申请日：2023-09-20

    Applicant: Collins Engine Nozzles, Inc.

    Inventor： Jason A. Ryon ,  Philip E. O. Buelow ,  Andy W. Tibbs ,  Brandon P. Williams

    IPC: F02C7/232 ,  F23R3/28

    Abstract: A valve system includes a spin chamber having an outlet drain configured to allow flow out of the spin chamber. A main spin surface of the spin chamber is defined around the outlet drain. A directional jet system is in fluid communication with the spin chamber. The directional jet system includes a member that is configured to move between a first position for directing a tangential flow around the drain, and a second position for directing a radial flow toward the drain.

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