公开(公告)号：US10443407B2

公开(公告)日：2019-10-15

申请号：US15043900

申请日：2016-02-15

Applicant: General Electric Company

Inventor： Robert David Briggs ,  Shawn Michael Pearson ,  Andrew David Kemp ,  Gulcharan Singh Brainch

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

Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.

公开(公告)号：US09896970B2

公开(公告)日：2018-02-20

申请号：US14928077

申请日：2015-10-30

Applicant: General Electric Company

Inventor： Kyle Andrew Grose ,  Arjan Johannes Hegeman ,  Andrew David Kemp ,  John Michael Pyles

IPC: F01D25/24 ,  F02C7/25

CPC classification number: F01D25/24 ,  F02C7/25 ,  Y02T50/672 ,  G07F17/34 ,  G07F17/3202 ,  A63F5/0094 ,  A63F5/045 ,  A63F5/00 ,  A63F5/0011 ,  A63F5/046 ,  A63F11/0011

Abstract: A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.

公开(公告)号：US20170234145A1

公开(公告)日：2017-08-17

申请号：US15043900

申请日：2016-02-15

Applicant: General Electric Company

Inventor： Robert David Briggs ,  Shawn Michael Pearson ,  Andrew David Kemp ,  Gulcharan Singh Brainch

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

CPC classification number: F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2260/2212 ,  Y02T50/672 ,  Y02T50/676

Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.