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    GAS TURBINE ENGINE WITH A COMPRESSED AIRFLOW INJECTION ASSEMBLY
    2.
    发明公开
    GAS TURBINE ENGINE WITH A COMPRESSED AIRFLOW INJECTION ASSEMBLY 审中-公开

    公开(公告)号：US20230323834A1

    公开(公告)日：2023-10-12

    申请号：US17841868

    申请日：2022-06-16

    Applicant: General Electric Company

    Inventor： Ravish Karve ,  Vishnu Vardhan Venkata Tatiparthi ,  Trevor Howard Wood

    IPC: F02K3/00 ,  F02C7/04

    CPC classification number: F02K3/00 ,  F02C7/04

    Abstract: A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including: a turbomachine; a fan rotatable by the turbomachine, the fan including a plurality of fan blades; a plurality of outlet guide vanes located downstream of the plurality of fan blades of the fan; a casing surrounding the plurality of fan blades or surrounding at least in part the turbomachine, the casing defining an opening at a location upstream of the plurality of outlet guide vanes; and a compressed airflow injection assembly positioned at least partially within the casing and configured to provide a flow of compressed airflow through the opening in a repeating pattern during an operating condition of the gas turbine engine.

    Object direction mechanism for turbofan engine
    3.
    发明授权
    Object direction mechanism for turbofan engine 有权

    公开(公告)号：US11767790B2

    公开(公告)日：2023-09-26

    申请号：US17408786

    申请日：2021-08-23

    Applicant: General Electric Company

    Inventor： Arthur William Sibbach ,  Brandon Wayne Miller

    IPC: F02K3/00 ,  F02C7/05 ,  F02C6/20 ,  F02C7/04

    CPC classification number: F02C7/05 ,  F02C6/20 ,  F02C7/04 ,  F02K3/00 ,  F05D2220/36

    Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for directing incoming objects towards an outer portion of the turbofan engine in communication with the inlet pre-swirl feature.

    TURBOFAN GAS TURBINE ENGINE
    4.
    发明申请
    TURBOFAN GAS TURBINE ENGINE 有权

    公开(公告)号：US20220112838A1

    公开(公告)日：2022-04-14

    申请号：US17484771

    申请日：2021-09-24

    Applicant: ROLLS-ROYCE plc

    Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

    IPC: F02C7/08 ,  F02K3/00

    Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes fan blades defining a corresponding fan area (AFAN). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and includes radially-extending vanes arranged in a circumferential array with at least one vane including a heat transfer element for heat transfer from a first fluid contained within each element to an airflow passing over a surface of each heat transfer element before entering the fan assembly inlet. Each heat transfer element extends axially along the corresponding vane, with a swept heat transfer element area (AHTE) being the wetted surface area of all heat transfer elements in contact with the airflow. A Fan to Element Area parameter FEA of AHTE/AFAN lies in the range of 47 to 132.

    Offset cores for gas turbine engines
    5.
    发明授权
    Offset cores for gas turbine engines 有权

    公开(公告)号：US10415466B2

    公开(公告)日：2019-09-17

    申请号：US14921575

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill

    IPC: F02C3/14 ,  F02C3/04 ,  F02K3/00 ,  F01D25/24 ,  F01D25/30 ,  F02K3/04 ,  F02C3/10

    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.

    Rotor shaft architectures for a gas turbine engine and methods of assembly thereof
    6.
    发明授权
    Rotor shaft architectures for a gas turbine engine and methods of assembly thereof 有权

    公开(公告)号：US10392970B2

    公开(公告)日：2019-08-27

    申请号：US15341838

    申请日：2016-11-02

    Applicant: General Electric Company

    Inventor： Bugra Han Ertas ,  Brandon Wayne Miller

    IPC: F01D25/16 ,  F01D5/02 ,  F01D15/12 ,  F04D29/053 ,  F04D29/056 ,  F04D29/32 ,  F02K3/00 ,  F02C7/06 ,  F02K3/06

    Abstract: A shaft assembly for a rotary machine, the rotary machine includes a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine. The shaft assembly includes an outer shaft configured to couple the high pressure compressor to the high pressure turbine. The outer shaft includes a first forward bearing assembly positioned forward of the high pressure compressor, and a first aft bearing assembly positioned between the high pressure compressor and the high pressure turbine. The shaft assembly also includes an inner shaft rotatable about a common axis with the outer shaft that at least partially extends about the inner shaft. The inner shaft is configured to couple the low pressure compressor to the low pressure turbine. The inner shaft includes a second forward bearing assembly positioned forward of the low pressure compressor, and a second aft bearing assembly positioned proximate the high pressure turbine.

    Gas turbine engine airfoil
    7.
    发明授权
    Gas turbine engine airfoil 有权

    公开(公告)号：US10370974B2

    公开(公告)日：2019-08-06

    申请号：US14836577

    申请日：2015-08-26

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F01D5/14 ,  F01D5/02 ,  F02C3/107 ,  F02K3/00

    Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.

    FAN MODULE HAVING VARIABLE-PITCH BLADES FOR A TURBINE ENGINE
    8.
    发明申请
    FAN MODULE HAVING VARIABLE-PITCH BLADES FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20190003484A1

    公开(公告)日：2019-01-03

    申请号：US16068102

    申请日：2016-12-22

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Serge Rene MORREALE ,  Yanis BENSLAMA ,  Jeremy DIEVART ,  Dominik IGEL

    IPC: F04D29/36 ,  F04D29/32 ,  F02K3/00 ,  F04D29/056 ,  F01D7/00

    Abstract: The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).

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