Invention Grant
- Patent Title: Circumferentially and axially staged can combustor for gas turbine engine
-
Application No.: US15025827Application Date: 2014-10-20
-
Publication No.: US10330321B2Publication Date: 2019-06-25
- Inventor: Timothy S. Snyder
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: O'Shea Getz P.C.
- International Application: PCT/US2014/061366 WO 20141020
- International Announcement: WO2015/061217 WO 20150430
- Main IPC: F23R3/12
- IPC: F23R3/12 ; F23R3/34 ; F23R3/46
Abstract:
A combustor section for a gas turbine engine includes a can combustor with a combustion chamber. A pilot fuel injection system is in axial communication with the combustion chamber. A main fuel injection system is in radial communication with the combustion chamber. The main fuel injection system includes a multiple of first main fuel nozzles that circumferentially alternate with a multiple of second main fuel nozzles.
Public/Granted literature
- US20160298852A1 CIRCUMFERENTIALLY AND AXIALLY STAGED CAN COMBUSTOR FOR GAS TURBINE ENGINE Public/Granted day:2016-10-13
Information query
