Solar Turbines Inc.

Peter Sykes

Bruno Enriquez Struck

Robert F Corr

Rajeshriben Patel

Alexander Ilich Krichever

Christian Di Norscia

Hanjie Lee

Kenneth Gregory Thomas

Robert Fanella

German Verduzco

Vu Phi

Timothy James Caron

Richard Braeutigam

Danny Gauce

Fuel injection for hydrogen-gas fuels poses risks with regard to emissions, flashback, and flame-holding events in a gas turbine engine. Accordingly, embodiments of a fuel injection system are disclosed that uniformly mix gas and fuel, while stabilizing a flame and facilitating maintenance. The fuel injection system may comprise a plurality of micromixer panels, mounted in windows of a frame that are arranged circumferentially around a longitudinal axis of the gas turbine engine. Each micromixer panel may comprise a plurality of axial channels, arranged around a central pilot body that is fixed in a grommet. Two or more internal fuel feeds may supply fuel to distinct subsets of fuel jets within the outlets of the axial channels, such that the fuel injection system may be operated in multiple stages.

Fuel injector panels having micromixers

A combustor liner may include an annular inner liner and an annular outer liner with a plurality of air holes thereon. The outer liner may be positioned circumferentially around the inner liner such that an annular cooling space is defined between the inner and the outer liner. The combustor liner may also include at least one resonator coupled to the outer liner such that a base of the resonator is separated from the outer liner to form a gap with an external surface of the outer liner. The combustor liner may also include a throat extending from the base of the resonator penetrating the inner liner and the outer liner. The combustor liner may further include a grommet assembly that allows for relative thermal expansion between the inner liner and the outer liner proximate the throat.

Gas turbine combustor with mounting for Helmholtz resonators

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Encinitas, CA, United States of America

Peter Sykes