公开(公告)号：US11549463B2

公开(公告)日：2023-01-10

申请号：US17181773

申请日：2021-02-22

Applicant: General Electric Company

Inventor： Vinod Shashikant Chaudhari ,  Bhaskar Nanda Mondal ,  Tsuguji Nakano ,  David W. Crall

IPC: F02K3/072 ,  F02C3/04 ,  F02C3/08 ,  F02K3/04 ,  F02C7/36 ,  F01D5/02 ,  F02C6/20

Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

公开(公告)号：US11262144B2

公开(公告)日：2022-03-01

申请号：US15858453

申请日：2017-12-29

Applicant: General Electric Company

Inventor： Andrew Breeze-Stringfellow ,  Daniel Lawrence Tweedt ,  Tsuguji Nakano ,  Syed Arif Khalid

IPC: F28F13/08 ,  F28D21/00 ,  F02C7/12 ,  F02C7/14 ,  F28D7/00 ,  F28F1/22 ,  F28D7/10

Abstract: A heat exchanger apparatus includes: spaced-apart peripheral walls extending between an inlet and an outlet, the peripheral walls collectively defining a flow channel which includes a diverging portion downstream of the inlet, in which a flow area is greater than a flow area at the inlet; a plurality of spaced-apart fins disposed in the flow channel, each of the fins having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the fins divide at least the diverging portion of the flow channel into a plurality of side-by-side flow passages; and a heat transfer structure disposed within at least one of the fins.

公开(公告)号：US11231043B2

公开(公告)日：2022-01-25

申请号：US15900891

申请日：2018-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Bhaskar Nanda Mondal ,  Jagata Laxmi Narasimharao ,  Tsuguji Nakano ,  Subramanian Narayanan

IPC: F04D29/32 ,  F01D5/06 ,  F01D25/24 ,  F04D19/02 ,  F01D5/14 ,  F02C3/04

Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.

公开(公告)号：US10815886B2

公开(公告)日：2020-10-27

申请号：US15625101

申请日：2017-06-16

Applicant: General Electric Company

Inventor： Christopher James Kroger ,  Brandon Wayne Miller ,  Trevor Wayne Goerig ,  David William Crall ,  Tsuguji Nakano ,  Jeffrey Donald Clements ,  Bhaskar Nanda Mondal

IPC: F02C7/05 ,  F02C3/04 ,  F02K3/06 ,  F04D29/52 ,  F04D29/68 ,  F02C7/04 ,  F04D29/54 ,  F02C7/057 ,  F02C7/042

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes a drive turbine and is located downstream of the compressor section. The gas turbine engine also includes a fan mechanically coupled to and rotatable with the drive turbine such that the fan is rotatable by the drive turbine at the same rotational speed as the drive turbine, the fan defining a fan pressure ratio and including a plurality of fan blades, each fan blade defining a fan tip speed. During operation of the gas turbine engine at a rated speed, the fan pressure ratio of the fan is less than 1.5 and the fan tip speed of each of the fan blades is greater than 1,250 feet per second.

公开(公告)号：US20200263547A1

公开(公告)日：2020-08-20

申请号：US16280531

申请日：2019-02-20

Applicant: General Electric Company

Inventor： Alan Roy Stuart ,  Tsuguji Nakano ,  Thomas Ory Moniz ,  Andrew Breeze-Stringfellow ,  Richard Schmidt

IPC: F01D5/06

Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.

公开(公告)号：US20170226960A1

公开(公告)日：2017-08-10

申请号：US15018893

申请日：2016-02-09

Applicant: General Electric Company

Inventor： Tsuguji Nakano ,  Andrew Breeze-Stringfellow

IPC: F02K1/68 ,  F02K1/76

CPC classification number: F02K1/68 ,  F02C9/18 ,  F02K1/66 ,  F02K1/766 ,  F02K3/075

Abstract: A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.

公开(公告)号：US20170089217A1

公开(公告)日：2017-03-30

申请号：US14870300

申请日：2015-09-30

Applicant: General Electric Company

Inventor： Swati Saxena ,  Andrew Breeze-Stringfellow ,  Rajkeshar Vijayraj Singh ,  Tsuguji Nakano

IPC: F01D25/02 ,  F02C3/04

CPC classification number: F04D27/02 ,  F01D25/02 ,  F02C3/04 ,  F04D29/526 ,  F04D29/681 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2250/294

Abstract: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.