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    GAS TURBINE ENGINE WITH IDLE THRUST RATIO
    11.
    发明申请
    GAS TURBINE ENGINE WITH IDLE THRUST RATIO 有权

    公开(公告)号：US20230028552A1

    公开(公告)日：2023-01-26

    申请号：US17379202

    申请日：2021-07-19

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Stephen G. Pixton ,  Gary Collopy ,  Ozhan Turgut

    IPC: F01D15/12 ,  F02C3/00 ,  F02C7/32

    Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a fan section including a fan having a plurality of fan blades and including an outer housing surrounding the fan blades to establish a bypass duct, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a fan drive turbine, the fan drive turbine driving the fan through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.

    HIGH AND LOW SPOOL CONFIGURATION FOR A GAS TURBINE ENGINE
    12.
    发明申请
    HIGH AND LOW SPOOL CONFIGURATION FOR A GAS TURBINE ENGINE 有权

    公开(公告)号：US20230022122A1

    公开(公告)日：2023-01-26

    申请号：US17379308

    申请日：2021-07-19

    Applicant: Raytheon Technologies Corporation

    Inventor： Stephen G. Pixton ,  Matthew R. Feulner ,  Marc J. Muldoon ,  Xinwen Xiao

    IPC: F02C7/36

    Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.

    Gas turbine engine with higher low spool torque-to-thrust ratio
    13.
    发明授权
    Gas turbine engine with higher low spool torque-to-thrust ratio 有权

    公开(公告)号：US12123356B2

    公开(公告)日：2024-10-22

    申请号：US17379233

    申请日：2021-07-19

    Applicant: Raytheon Technologies Corporation

    Inventor： Stephen G. Pixton ,  Karl L. Hasel

    IPC: F02C3/06 ,  F02C7/36

    CPC classification number: F02C7/36 ,  F05D2220/323 ,  F05D2260/40311

    Abstract: A gas turbine engine includes a fan drive turbine driving a low pressure compressor, and driving a gear reduction to in turn drive a fan rotor at a speed slower than the fan drive turbine. The turbine section further includes a high pressure turbine driving the high pressure compressor. The fan drive turbine and low pressure compressor are connected by a shaft and the fan drive turbine, the shaft and the low pressure compressor define a low pressure spool. The gas turbine engine is rated to provide an amount of thrust at maximum takeoff, and a low spool thrust ratio defined as a ratio of a torque on the low pressure spool at maximum takeoff in ft-lbs and the maximum takeoff thrust being defined in lbf, with the low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf, and less than or equal to 1.2 ft-lb/lbf.

    GAS TURBINE ENGINE WITH HIGH LOW SPOOL POWER EXTRACTION RATIO
    15.
    发明申请
    GAS TURBINE ENGINE WITH HIGH LOW SPOOL POWER EXTRACTION RATIO 有权

    公开(公告)号：US20230029308A1

    公开(公告)日：2023-01-26

    申请号：US17379244

    申请日：2021-07-19

    Applicant: Raytheon Technologies Corporation

    Inventor： Stephen G. Pixton ,  Karl L. Hasel

    IPC: F01D15/12 ,  F02C3/06

    Abstract: A gear reduction drives a fan rotor at a speed slower than a fan drive turbine. The turbine section further includes a high pressure turbine driving a high pressure compressor. The fan drive turbine and low pressure compressor are connected by a shaft and the low pressure turbine. The shaft and the low pressure compressor define a low pressure spool, the low pressure spool has a torque at maximum takeoff defined in ft-lbs and also having a low pressure spool power defined in horsepower and at maximum takeoff, and a ratio of the low pressure spool torque to the low pressure spool power being defined, with the low pressure spool power being defined in horsepower, and the ratio of the low pressure spool torque to the low pressure spool power being greater than or equal to 0.6 ft-lb/hp and less than or equal to 1.2 ft-lb/hp.

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