Bearing outer race retention during high load events

    公开(公告)号:US10196980B2

    公开(公告)日:2019-02-05

    申请号:US15017805

    申请日:2016-02-08

    Abstract: A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. A plurality of edge recesses are defined in the bearing housing and a plurality of lug tabs extending radially from the engine's interface shell limit are disposed in the edge recess to limit the deflection and self-arrest the distortion of the retention housing. A gas turbine engine includes the retention housing described above.

    Mounting assembly for a gearbox assembly

    公开(公告)号:US12281618B2

    公开(公告)日:2025-04-22

    申请号:US18910905

    申请日:2024-10-09

    Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

    SEAL FOR A GAS TURBINE ENGINE
    125.
    发明申请

    公开(公告)号:US20250116199A1

    公开(公告)日:2025-04-10

    申请号:US18984554

    申请日:2024-12-17

    Abstract: Seals for a gas turbine engine are disclosed herein. An example sealing apparatus for a gas turbine engine includes a first end having a first contact surface to contact a first component of a rotating machine, a second end having a second contact surface to contact a second component of the rotating machine, the second component positioned in proximity to the first component such that a cavity is formed therebetween, the apparatus dividing the cavity into a first cavity portion and a second cavity portion, and a central portion extending the first end from the second end, the central portion defining a first chamber and a second chamber, the first chamber in fluid communication with the first cavity portion, the second chamber in fluid communication with the second cavity portion, the first chamber is fluidly isolated from the second chamber.

    Variable flowpath casings for blade tip clearance control

    公开(公告)号:US12270308B2

    公开(公告)日:2025-04-08

    申请号:US18493508

    申请日:2023-10-24

    Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.

    Compliant shroud designs with variable stiffness

    公开(公告)号:US12221892B2

    公开(公告)日:2025-02-11

    申请号:US18463970

    申请日:2023-09-08

    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

    Variable bleed valve assemblies
    129.
    发明授权

    公开(公告)号:US12180890B1

    公开(公告)日:2024-12-31

    申请号:US18454531

    申请日:2023-08-23

    Abstract: Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion.

    FACE SEAL ROBUST TO CASING VIBRATION

    公开(公告)号:US20240426222A1

    公开(公告)日:2024-12-26

    申请号:US18751022

    申请日:2024-06-21

    Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.

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