公开(公告)号：US20210310376A1

公开(公告)日：2021-10-07

申请号：US16838345

申请日：2020-04-02

Applicant: General Electric Company

Inventor： Jonathan Ong ,  Christian Thomas Wakelam ,  Andreas Peters

IPC: F01D25/24 ,  F01D25/28

Abstract: Aspects of the disclosure generally relate to a turbine center frame for a turbine engine through which a flow path extends. The turbine center frame can include an inner wall radially spaced from an outer wall, with the inner and outer walls extending between an inlet and an outlet, and with the outlet downstream of the inlet with respect to the flow path. A set of circumferentially-spaced airfoils can extend between the inner wall and the outer wall.

公开(公告)号：US20210276262A1

公开(公告)日：2021-09-09

申请号：US17329301

申请日：2021-05-25

Applicant: General Electric Company

Inventor： Christian Wakelam ,  Rene du Cauze de Nazelle ,  Christian Aalburg ,  Florian Hoefler ,  Jonathan Ong

IPC: B29C64/371 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B29C64/153 ,  B29C64/25 ,  B29C64/264 ,  B28B1/00 ,  B29C64/245 ,  B22F12/00 ,  B22F10/00

Abstract: An additive manufacturing (AM) system includes a housing defining a chamber and a build platform disposed in a lower portion of the chamber. The AM system includes an upper gas inlet disposed in a side-wall and in an upper portion of the chamber and configured to supply an upper gas flow parallel to the build platform. The AM system includes a lower gas inlet in the lower portion of the chamber, wherein the lower gas inlet includes one or more pairs of dividing walls extending from the side-wall toward the build platform and configured to guide the lower gas flow at one or more flow angles with respect to the build platform. The AM system includes at least one gas delivery mechanisms to regulate flow characteristics of the upper and lower gas flows, and includes a gas outlet to discharge the upper and lower gas flows from the chamber.

公开(公告)号：US20210270137A1

公开(公告)日：2021-09-02

申请号：US17148635

申请日：2021-01-14

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：US20190322051A1

公开(公告)日：2019-10-24

申请号：US15961602

申请日：2018-04-24

Applicant: General Electric Company

Inventor： Christian Wakelam ,  Rene du Cauze de Nazelle ,  Christian Aalburg ,  Florian Hoefler ,  Jonathan Ong

IPC: B29C64/371 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B29C64/153 ,  B29C64/245 ,  B29C64/25 ,  B29C64/264 ,  B22F3/105 ,  B28B1/00

Abstract: An additive manufacturing (AM) system includes a housing defining a chamber and a build platform disposed in a lower portion of the chamber. The AM system includes an upper gas inlet disposed in a side-wall and in an upper portion of the chamber and configured to supply an upper gas flow parallel to the build platform. The AM system includes a lower gas inlet in the lower portion of the chamber, wherein the lower gas inlet includes one or more pairs of dividing walls extending from the side-wall toward the build platform and configured to guide the lower gas flow at one or more flow angles with respect to the build platform. The AM system includes at least one gas delivery mechanisms to regulate flow characteristics of the upper and lower gas flows, and includes a gas outlet to discharge the upper and lower gas flows from the chamber.

公开(公告)号：US12071889B2

公开(公告)日：2024-08-27

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: F02C3/06 ,  F02C3/067 ,  F02C7/14 ,  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：US11014304B2

公开(公告)日：2021-05-25

申请号：US15961602

申请日：2018-04-24

Applicant: General Electric Company

Inventor： Christian Wakelam ,  Rene du Cauze de Nazelle ,  Christian Aalburg ,  Florian Hoefler ,  Jonathan Ong

IPC: B29C64/371 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  B29C64/153 ,  B29C64/245 ,  B29C64/25 ,  B29C64/264 ,  B28B1/00 ,  B22F10/00 ,  B22F10/10

Abstract: An additive manufacturing (AM) system includes a housing defining a chamber and a build platform disposed in a lower portion of the chamber. The AM system includes an upper gas inlet disposed in a side-wall and in an upper portion of the chamber and configured to supply an upper gas flow parallel to the build platform. The AM system includes a lower gas inlet in the lower portion of the chamber, wherein the lower gas inlet includes one or more pairs of dividing walls extending from the side-wall toward the build platform and configured to guide the lower gas flow at one or more flow angles with respect to the build platform. The AM system includes at least one gas delivery mechanisms to regulate flow characteristics of the upper and lower gas flows, and includes a gas outlet to discharge the upper and lower gas flows from the chamber.

公开(公告)号：US20170298747A1

公开(公告)日：2017-10-19

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

CPC classification number: F01D9/023 ,  F01D5/143 ,  F01D5/145 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/20 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/32 ,  Y02T50/671 ,  Y02T50/673

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 50% 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：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：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.