公开(公告)号：US20180306120A1

公开(公告)日：2018-10-25

申请号：US15493549

申请日：2017-04-21

Applicant: General Electric Company

Inventor： Jinjie Shi ,  Stephen Gerard Schadewald ,  Jason Paul Hoppa ,  Kirk Douglas Gallier ,  Christopher Edward Wolfe ,  Robert Proctor

IPC: F02C7/28 ,  F16J15/16 ,  F16J15/34 ,  F02C3/04 ,  F23R3/00 ,  F01D9/02 ,  F02C9/18

CPC classification number: F02C7/28 ,  F01D9/02 ,  F02C3/04 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/58 ,  F16J15/164 ,  F16J15/34 ,  F23R3/002

Abstract: A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (Phigh) bypass airflow exiting a compressor to the cavity. The high-pressure (Phigh) bypass airflow exerting a radial force on the piston ring.

公开(公告)号：US20180016924A1

公开(公告)日：2018-01-18

申请号：US15212337

申请日：2016-07-18

Applicant: General Electric Company

Inventor： Kirk Douglas Gallier ,  Charles William Craig, III

IPC: F01D9/04 ,  F01D5/02 ,  F01D25/24 ,  F01D5/12 ,  F01D25/00

CPC classification number: F01D25/246 ,  F01D9/042 ,  F01D11/005 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one embodiment, a shroud segment for a gas turbine engine having a rotor blade stage and a nozzle stage is provided. The shroud segment comprises a forward end defining an outer wall of the rotor blade stage and an aft end defining an outer wall of the nozzle stage. The aft end defines at least a portion of an opening therethrough for receipt of a nozzle, and the forward end and the aft end form a single, continuous component. In another embodiment, a gas turbine engine is provided, having a shroud with a forward end positioned near a leading edge of a plurality of rotor blades of a rotor blade stage and an aft end positioned near a trailing edge of a plurality of nozzles of a nozzle stage. Methods of assembling a gas turbine engine also are provided.

公开(公告)号：US20170328216A1

公开(公告)日：2017-11-16

申请号：US15151838

申请日：2016-05-11

Applicant: General Electric Company

Inventor： Kirk Douglas Gallier

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04 ,  F01D25/00

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/188 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2260/202 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer surface of the airfoil. The airfoil further includes opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges. The airfoil also includes a filler pack defining the trailing edge; the filler pack comprises a ceramic matrix composite material. Moreover, the airfoil includes a plenum defined within the airfoil for receiving a flow of cooling fluid, and a cooling passage defined within the filler pack for directing the flow of cooling fluid from the plenum to the outer surface of the airfoil. Methods for forming airfoils for gas turbine engines also are provided.

公开(公告)号：US20170107837A1

公开(公告)日：2017-04-20

申请号：US14887537

申请日：2015-10-20

Applicant: General Electric Company

Inventor： Benjamin Scott Huizenga ,  Kevin Robert Feldmann ,  Robert Alan Frederick ,  Robert Charles Groves, II ,  Kirk Douglas Gallier ,  Timothy Francis Andrews ,  Darrell Senile

IPC: F01D11/00 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D11/005 ,  F01D5/284 ,  F01D9/023 ,  F01D9/041 ,  F01D9/047 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/57 ,  F05D2250/71 ,  F05D2300/6033 ,  F16J15/061 ,  F16J15/0887 ,  Y02T50/672

Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.

公开(公告)号：US20240301798A1

公开(公告)日：2024-09-12

申请号：US18668840

申请日：2024-05-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Daniel Endecott Osgood ,  Kirk Douglas Gallier

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/187 ,  F01D5/087 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/232

Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

公开(公告)号：US11998974B2

公开(公告)日：2024-06-04

申请号：US17898751

申请日：2022-08-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Craig Alan Gonyou ,  Daniel Lee Durstock ,  Kevin R. Feldmann ,  Kirk Douglas Gallier ,  William C. Herman ,  Nicholas Charles Gentilli

IPC: B22C9/10

CPC classification number: B22C9/10

Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:





(


D
⁢

1

eq
⁢
min




D
⁢

2

eq
⁢
min




)

⁢


(

R

D
⁢

2

eq
⁢
min




)

.

公开(公告)号：US11927111B2

公开(公告)日：2024-03-12

申请号：US17836023

申请日：2022-06-09

Applicant: General Electric Company

Inventor： Jonathan Michael Rausch ,  Zachary Daniel Webster ,  Kevin Robert Feldmann ,  Andrew David Perry ,  Kirk Douglas Gallier ,  Daniel Endecott Osgood

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.

公开(公告)号：US20230399954A1

公开(公告)日：2023-12-14

申请号：US17836049

申请日：2022-06-09

Applicant: General Electric Company

Inventor： Jonathan Michael Rausch ,  Zachary Daniel Webster ,  Kevin Robert Feldmann ,  Andrew David Perry ,  Kirk Douglas Gallier ,  Daniel Endecott Osgood

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2260/202 ,  F05D2240/30

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

公开(公告)号：US11598216B2

公开(公告)日：2023-03-07

申请号：US16700017

申请日：2019-12-02

Applicant: General Electric Company

Inventor： Kirk Douglas Gallier ,  Darrell Glenn Senile ,  John Calhoun

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28 ,  B28B23/00 ,  B32B37/14 ,  B32B38/10 ,  B32B38/08 ,  B32B38/00 ,  F01D9/04 ,  F01D25/00 ,  F01D25/12

Abstract: Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

公开(公告)号：US11519277B2

公开(公告)日：2022-12-06

申请号：US17231263

申请日：2021-04-15

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Kirk Douglas Gallier ,  Gregory Terrence Garay ,  Zachary Daniel Webster ,  Daniel Lee Durstock ,  Ricardo Caraballo

IPC: F01D5/18

Abstract: An airfoil for a turbine engine having a working airflow separated into a cooling airflow and a combustion airflow, the airfoil comprising a wall defining an interior and having an outer surface over which flows the combustion airflow, the outer surface defining a first side and a second side extending between a leading edge and a trailing edge to define a chord-wise direction; at least one cooling conduit located within the interior and fluidly coupled to the cooling airflow. A primary cooling passage having at least one inlet fluidly coupled to the at least one cooling conduit, a primary outlet on the outer surface. A passage connecting the at least one inlet to the primary outlet, the passage separated into a first portion and a second portion. The primary outlet spaced from the trailing edge a predetermined distance.