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    GAS TURBINE ENGINE WITH MID-COMPRESSOR BLEED
    21.
    发明申请
    GAS TURBINE ENGINE WITH MID-COMPRESSOR BLEED 审中-公开

    公开(公告)号：US20190145420A1

    公开(公告)日：2019-05-16

    申请号：US15810214

    申请日：2017-11-13

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F04D27/02 ,  F04D29/54 ,  F01D17/10 ,  F02C6/08 ,  F02C9/18

    Abstract: A gas turbine engine for an aircraft includes a fan section, a turbine section, a compressor section, and an engine bleed system. The compressor section includes a low compressor stage proximate to the fan section, a high compressor stage axially downstream from the low compressor stage and proximate to the turbine section, and a mid-compressor stage including variable vane assemblies distributed axially between the low and high compressor stage. The engine bleed system includes engine bleed taps with a mid-compressor bleed tap axially between two of the variable vane assemblies, at least one low stage bleed tap axially upstream from the mid-compressor bleed tap, and at least one high stage bleed tap axially downstream from the mid-compressor bleed tap. An external manifold is in pneumatic communication with the mid-compressor bleed tap. A valve system can select one engine bleed tap as a bleed air source for an aircraft use.

    Three spool turbofan engine with low noise intermediate turbine rotor
    23.
    发明授权
    Three spool turbofan engine with low noise intermediate turbine rotor 有权

    公开(公告)号：US10233774B2

    公开(公告)日：2019-03-19

    申请号：US14905994

    申请日：2014-07-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Bruce L. Morin

    IPC: F01D25/04 ,  F04D29/32 ,  F01D15/12 ,  F01D9/06 ,  F01D5/06 ,  F01D17/10 ,  F02C3/107 ,  F01D5/14 ,  F02K3/06

    Abstract: A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of blades×speed)/60?5500 Hz.

    LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT
    25.
    发明申请
    LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT 审中-公开

    公开(公告)号：US20190039740A1

    公开(公告)日：2019-02-07

    申请号：US16152929

    申请日：2018-10-05

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: B64D13/06 ,  F02C7/20 ,  F02K3/04 ,  F02C6/08 ,  B64D27/26

    Abstract: A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.

    Geared turbofan engine with inter-shaft deflection feature
    27.
    发明授权
    Geared turbofan engine with inter-shaft deflection feature 有权

    公开(公告)号：US10190495B2

    公开(公告)日：2019-01-29

    申请号：US14433779

    申请日：2013-03-12

    Applicant: United Technologies Corporation

    Inventor： Pedro Laureano ,  Frederick M. Schwarz

    IPC: F01D5/02 ,  F02C3/10 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F04D29/054 ,  F01D21/04

    Abstract: A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a first turbine driving the first compressor and a second turbine driving the second compressor. An inner shaft defines a driving link between the second compressor and the second turbine and an outer shaft defines a driving link between the first compressor and the first turbine. The inner shaft and the outer shaft are concentric about a common axis of rotation. A bumper is disposed on the inner shaft within an axial region common to an aft portion of the outer shaft for accommodating interaction between the inner and outer shafts during high load conditions.

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