Fuel manifold inlet tube
AssigneePratt & Whitney Canada Corp.
InventorJason Fish
Life of this patent
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Abstract
In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, the side inlet being sealingly isolated by at least two annular sealing members concentric with each other and disposed about the tube body at longitudinally spaced part points thereon.
Claims10
An inlet tube for supplying fuel to a manifold of a combustor in a gas turbine engine, the inlet tube comprising:
- a tube body having first and second ends;
- a first longitudinal channel defined in the tube body, the first longitudinal channel having an outlet in fluid communication with the manifold and a side feed inlet located in an outer surface of the tube body between the first and second ends, the side feed inlet being disposed within a first circumferential groove defined in the outer surface, the first circumferential groove forming a first circumferential channel when the inlet tube is received within a mating part of an engine casing;
- and
- two O-rings concentric with each other and disposed about the tube body at longitudinally spaced apart points thereon, the two O-rings being disposed on opposite sides of the side feed inlet of the first longitudinal channel to sealingly enclose the side feed inlet between the two O-rings when the tube body is received within said mating part.
An inlet tube for supplying fuel to a manifold of a combustor in a gas turbine engine, the inlet tube comprising a tube body having means for providing fluid flow communication between first and second ends of the tube body, the second end of the tube body being for engagement with the manifold, and means for sealingly isolating two side fuel inlets disposed in respective circumferential groves in the tube body proximate said first end, said circumferential grooves each forming a separate enclosed circumferential channel when the inlet tube is received within a mating part of an engine casing, said two side fuel inlets being in fluid flow communication with said means for providing fluid flow communication between the first and second ends of the tube body, said means for sealingly isolating the two side fuel inlets being concentric with each other about the tube body.
A fuel manifold assembly for a combustor in a gas turbine engine, the fuel manifold assembly comprising:
- an internal fuel manifold having at least one fuel flow passage;
- and
- an inlet tube having a tube body extending between a first and a second end, the first end being engaged with the internal fuel manifold, first and second fuel channels extending through the tube body and each having an inlet and an outlet, the outlets being in fluid flow communication with said fuel flow passage of said internal fuel manifold, the inlets of said first and second fuel channels respectively being a first and a second side fuel inlet located in an outer surface of the tube body between said first and second ends, the first and second side fuel inlets being disposed within respective first and second circumferential grooves defined in the outer surface;
- and
- three O-rings concentric with each other and disposed about the tube body, the O-rings being longitudinally spaced apart to sealingly isolate the first and second side fuel inlets which are each respectively located between two of the three O-rings.
Dependencies are inferred from the claim text.