公开(公告)号：US10815805B2

公开(公告)日：2020-10-27

申请号：US15411592

申请日：2017-01-20

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Nicholas R. Dinsmore ,  Daniel Tyler Jarboe

IPC: F01D9/06 ,  F01D11/00 ,  F01D11/06

Abstract: A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.

公开(公告)号：US20180209299A1

公开(公告)日：2018-07-26

申请号：US15411549

申请日：2017-01-20

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Nicholas R. Dinsmore ,  Daniel Tyler Jarboe

IPC: F01D25/12 ,  F01D11/02 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D9/041 ,  F01D9/065 ,  F01D11/001 ,  F01D11/02 ,  F01D11/06 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/60

Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.

公开(公告)号：US20200157970A1

公开(公告)日：2020-05-21

申请号：US16715706

申请日：2019-12-16

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Nicholas R. Dinsmore ,  Daniel Tyler Jarboe

IPC: F01D25/12 ,  F01D9/04 ,  F01D11/02 ,  F01D11/00 ,  F01D11/06 ,  F01D9/06

Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.

公开(公告)号：US10544702B2

公开(公告)日：2020-01-28

申请号：US15411549

申请日：2017-01-20

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Nicholas R. Dinsmore ,  Daniel Tyler Jarboe

IPC: F01D25/12 ,  F01D11/02 ,  F01D9/04

Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.

公开(公告)号：US20180209300A1

公开(公告)日：2018-07-26

申请号：US15411592

申请日：2017-01-20

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Nicholas R. Dinsmore ,  Daniel Tyler Jarboe

IPC: F01D25/12 ,  F01D9/06 ,  F01D5/06 ,  F01D9/04 ,  F01D11/00

CPC classification number: F01D9/065 ,  F01D11/001 ,  F01D11/06

Abstract: A turbine interstage structure for a gas turbine engine that includes a first stage disk and a second stage disk. A central plenum is defined by a an inner band for supporting nozzle vanes, a forward stator plate and an aft stator plate wherein the forward stator plate is spaced-apart from the aft stator plate, and an inner boundary. A forward mid-seal positioned between the inner boundary and the forward stator plate. An aft mid-seal positioned between the inner boundary and the aft stator plate; and wherein the inner boundary is a solid annular component.