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：US20230059927A1

公开(公告)日：2023-02-23

申请号：US17979057

申请日：2022-11-02

Applicant: General Electric Company

Inventor： Christopher Ryan Johnson ,  Paul Hadley Vitt ,  Eric Joseph Schroeder ,  Carlos Gilberto Fernandez-Soto

IPC: F02C7/24

Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

公开(公告)号：US11125089B2

公开(公告)日：2021-09-21

申请号：US16534724

申请日：2019-08-07

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

Inventor： Francesco Bertini ,  Aspi Rustom Wadia ,  Lyle D. Dailey ,  Andrea Arnone ,  Filippo Rubechini ,  Matteo Giovannini ,  Paul Hadley Vitt ,  Jeffrey Donald Clements

IPC: F01D9/04 ,  F01D5/14

Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.

公开(公告)号：US10760426B2

公开(公告)日：2020-09-01

申请号：US15621123

申请日：2017-06-13

Applicant: General Electric Company

Inventor： Paul Hadley Vitt ,  Brian David Keith

IPC: F01D5/14 ,  F01D9/06 ,  F01D17/14

Abstract: An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.

公开(公告)号：US20200049014A1

公开(公告)日：2020-02-13

申请号：US16490416

申请日：2018-03-06

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

Inventor： Jeffrey Donald Clements ,  Paul Hadley Vitt ,  Francesco Bertini ,  Aspi Rustom Wadia ,  Ganesh Seshadri ,  Mahendran Manoharan ,  Ravikanth Avancha

IPC: F01D5/14 ,  F01D5/28

Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.

公开(公告)号：US10344602B2

公开(公告)日：2019-07-09

申请号：US15131292

申请日：2016-04-18

Applicant: General Electric Company

Inventor： Harjit Hura ,  Paul Hadley Vitt ,  Brian David Keith ,  Jonathan Ong

IPC: F01D9/02 ,  F02C3/04 ,  F02C7/20 ,  F01D5/14 ,  F01D9/06 ,  F04D29/54 ,  F04D29/58

Abstract: A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.

公开(公告)号：US10253637B2

公开(公告)日：2019-04-09

申请号：US14967069

申请日：2015-12-11

Applicant: General Electric Company

Inventor： Eric Joseph Schroeder ,  Paul Hadley Vitt ,  Timothy John Swenson ,  Kirk Douglas Gallier ,  Aspi Rustom Wadia

IPC: F02C7/12 ,  F01D5/20 ,  F01D5/14 ,  F01D9/04 ,  F02C3/06 ,  F02C7/18 ,  F01D5/18

Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.

公开(公告)号：US20190003323A1

公开(公告)日：2019-01-03

申请号：US15637791

申请日：2017-06-29

Applicant: General Electric Company

Inventor： Connor Marie Shirley ,  Harjit Singh Hura ,  Paul Hadley Vitt

IPC: F01D9/04 ,  F04D29/54

CPC classification number: F01D9/041 ,  F01D5/143 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/80 ,  F05D2250/20 ,  F05D2250/611

Abstract: A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.