United Technologies Corporation

Torence P Brogan

Jeffery A Lovett

Meredith Bright Colket, Iii

Christopher A Eckett

Donald J Hautman

Frank J Cunha

May L Corn

Jeffrey A Lovett

A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

Fuel delivery system with a cavity coupled fuel injector

A multi-stage vortex mixer for a combustor of a gas turbine engine includes a vortex amplifier stage in communication with a first stage amplifier, the vortex amplifier stage in communication with a dilution hole.

Multi-stage amplification vortex mixture for gas turbine engine combustor

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.

Engine hot section vane with tapered flame holder surface

A gas turbine engine augmenter has a gas flowpath. A number of vanes extend into the gas flowpath. A number of augmenter fuel conduits have outlets along at least some of the vanes. At least one burner discharge outlet is along at least one of the vanes for discharging a pilot gas.

Growing community of inventors

Manchester, CT, United States of America

Torence P Brogan