公开(公告)号：US11959393B2

公开(公告)日：2024-04-16

申请号：US17523505

申请日：2021-11-10

Applicant: GE Avio S.r.l. ,  General Electric Company

Inventor： Saurya Ranjan Ray ,  Francesco Bertini ,  Lyle Douglas Dailey ,  Jeffrey D. Clements ,  Jaikumar Loganathan ,  Simone Rosa Taddei

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2240/301 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/181 ,  F05D2250/711 ,  F05D2250/712

Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

公开(公告)号：US20230340906A1

公开(公告)日：2023-10-26

申请号：US17713649

申请日：2022-04-05

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH ,  GE Avio Srl

Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters ,  Jonathan Ong

IPC: F02C3/067 ,  F02C7/141 ,  F02C7/36

CPC classification number: F02C3/067 ,  F02C7/141 ,  F02C7/36 ,  F05D2220/60 ,  F05D2260/213 ,  F05D2260/40311

Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.

公开(公告)号：US20230130213A1

公开(公告)日：2023-04-27

申请号：US17876009

申请日：2022-07-28

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Ernesto Sozio ,  Francesco Bertini ,  Jeffrey Donald Clements ,  Jonathan Ong ,  Lyle Douglas Dailey ,  Paul Hadley Vitt ,  Matteo Renato Usseglio

IPC: F01D5/14

Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).

公开(公告)号：US20180347403A1

公开(公告)日：2018-12-06

申请号：US15609368

申请日：2017-05-31

Applicant: General Electric Company

Inventor： Mahendran Manoharan ,  Ganesh Seshadri ,  Robert J. Beacock ,  Lyle Douglas Dailey ,  Ravikanth Avancha

IPC: F01D25/26 ,  F02C3/04 ,  F01D9/04 ,  F01D5/02

Abstract: An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.