US Patent:
20130263572, Oct 10, 2013
Inventors:
Jeffery A. Lovett - Tolland CT, US
Donald J. Hautman - Marlborough CT, US
Torence P. Brogan - Manchester CT, US
Christopher A. Eckett - New Britain CT, US
Assignee:
UNITED TECHNOLOGIES CORPORATION - Hartford CT
International Classification:
F02C 7/264
Abstract:
A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end.