公开(公告)号：US20190072279A1

公开(公告)日：2019-03-07

申请号：US15694191

申请日：2017-09-01

Applicant: General Electric Company

Inventor： Jayaprakash Natarajan ,  Seth Reynolds Hoffman ,  Ronnie Ray Pentecost ,  Wei Zhao

IPC: F23R3/28

CPC classification number: F23R3/286 ,  F02C7/222 ,  F02C9/26 ,  F23R3/002 ,  F23R3/34 ,  F23R2900/00004

Abstract: A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.

公开(公告)号：US20170176015A1

公开(公告)日：2017-06-22

申请号：US14973375

申请日：2015-12-17

Applicant: General Electric Company

Inventor： Sravan Kumar Dheeraj Kapilavai ,  Wei Zhao ,  Shivakumar Srinivasan

IPC: F23R3/36 ,  F02C3/20 ,  F02C3/14 ,  F02C7/22

CPC classification number: F23R3/36 ,  F02C3/14 ,  F02C3/20 ,  F02C7/222 ,  F05D2220/32 ,  F05D2260/60 ,  F23R3/286 ,  F23R3/346

Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path. Each outlet is configured to inject a secondary fuel and compressed air into the primary compressed air flow path in a direction transverse to the primary compressed air flow path forming a fuel-air mixture.