Fuel nozzle with combined radial and axial bellows
AssigneeUnited Technologies Corporation
InventorsCharles Graves, Todd Neill, Raman Ras, Kiran Patwari, Robert T. Mains, Curtis H. Scheuerman
Life of this patent
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Abstract
A fuel nozzle for the combustor of gas turbine engines includes evacuated radial and axial bellows concentrically mounted to the fuel passages to prevent coking of the fuel passages and maintain the structural integrity of the integral parts and particularly the weld joints and the method of construction is disclosed.
Claims7
A fuel nozzle for a gas turbine engine including a generally cylindrical housing defining an axial central passage,
- First fuel delivery means including an axially extending tubular member having ends and having a first nozzle on one end and being disposed along the axis of said central passage defining a first passageway for delivering primary fuel.
- Second fuel delivery means including another tubular member having ends concentrically disposed relative to said axially extending tubular member including a second nozzle on one end defining a second passageway for delivering secondary fuel,
- said housing including a cylindrically shaped wall encapsulating said first passageway and said second passageway and defining with said other tubular member an annular evacuated chamber,
- an axial bellows attached to one end of said other tubular member remote from said second nozzle, and
- a radial bellows attached to said other tubular member adjacent said second nozzle,
- said first nozzle includes a complimentary tubular member defining an orifice for discharging primary fuel, and said second nozzle also includes another complementary tubular member defining another orifice for discharging secondary fuel and bonding means for joining said tubular member to said complementary tubular member and said other tubular member to said other complementary tubular member whereby said radial bellows relieves the thermal stress on said bonding means occasioned when said primary and/or secondary fuel flows through said orifice and/or said other orifice,
- said radial bellows includes a first annular wall concentrically disposed relative to said primary and secondary fuel passageways and a second annular wall concentrically disposed relative to said first annular wall and a convolute interconnecting said first annular wall and said second annular wall at one end and defining an open ended annular cavity for receiving ambient air therein,
In combination, a fuel nozzle and combustor for a gas turbine engine which engine includes a fan discharge duct and a shroud disposed between said fan discharge duct and said combustor, said combustor defining a combustion zone,
- said fuel nozzle having a generally cylindrical housing defining an axial central passage disposed about a longitudinal axis,
- means including an axially extending tubular member having ends and having a first nozzle on one end and being disposed in said axial central passage defining a first passageway for delivering primary fuel into said combustion zone.
- additional means including another tubular member having ends concentrically disposed relative to said axially extending tubular member including a second nozzle on one end defining a second passageway for delivering secondary fuel into said combustion zone,
- said housing including a cylindrically shaped wall encapsulating said first passageway and said second passageway and defining with said other tubular member an annular evacuated chamber whose pressure is substantially below the ambient pressure, an axial bellows forming a portion of said evacuated chamber attached to one end of said other tubular member remote from said second nozzle, and
- a radial bellows also forming a portion of said evacuated chamber having an axis normal to said longitudinal axis attached to said other tubular member adjacent said second nozzle.
Dependencies are inferred from the claim text.