Multiple passage cooling circuit for gas turbine fuel...

Details Multiple passage cooling circuit for gas turbine fuel... Multiple passage cooling circuit for gas turbine fuel...

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/28 (2006.01) F02M 53/04 (2006.01) F23D 11/36 (2006.01)

Patent

CA 2145633

A gas turbine fuel nozzle (11) and method of fuel flow provide resistance to coking of the fuel by means of a multiple passage heat transfer cooling circuit. Fuel streams to primary and secondary sprays of pilot (13) and main (15) nozzle tips are arranged to transfer heat between the pilot primary fuel stream and each of the main secondary fuel stream and the pilot secondary fuel stream. This protects the fuel in the streams from coking during both low flow, lower engine heat conditions and high flow, high engine heat conditions. This nozzle and flow can protect engines with both single tip and dual tip nozzles.

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