Title: Inlet for annular gas turbine combustor

Abstract: Combustion equipment for a gas turbine engine comprises an annular flame tube having a circumferential array of upstream projecting pots or vortex generators at its upstream end, an annular diffusing passageway located upstream of the pots and terminating adjacent the upstream ends of the pots, and a plurality of tubular ducts, one extending from the annular diffusing passageway to the upstream end of each pot.

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Inventors: Pask, George (Stanton-by-Bridge, GB)

Application Number: 862193
Filing Date: 1977-12-19
Publication_date: 1979-12-11
Assignee: Rolls-Royce Limited (London, GB2)
Primary Class(es): 60/804 60/751
Other Classes:
US Patent Ref:

3026675	Mar, 1962	Vesper et al.	60/39.
3372542	Mar, 1968	Sevetz	60/39.
3394543	Jul, 1968	Slattery	60/39.
3398529	Aug, 1968	Schmitz et al.	60/39.
3667221	Jun, 1972	Taylor	60/39.
3738106	Jun, 1973	Stein et al.	60/39.
3834159	Sep, 1974	Vdoviak	60/39.

Other Refs:
Primary Examiner: Croyle, Carlton R.
Assistant Examiner: Ross, Thomas I.
Attorney: Cushman, Darby & Cushman