Fuel nozzle assembly for a gas turbine engine

Claim 2

A fuel nozzle assembly for a gas turbine engine comprising: a fuel delivery tube having a fuel nozzle at one end and fuel inlet means at the opposite end; a support flange attached to said fuel delivery tube generally adjacent said inlet means for mounting said fuel delivery tube in said engine; an air delivery tube enclosing the portion of said fuel delivery tube extending from said support flange in spaced relation to define an annular air chamber therebetween, said air delivery tube terminating at one end in a wall defining an opening for receiving therein said nozzle of the fuel tube, and further defining a plurality of apertures through said wall and in communication with said air chamber for atomizing air passages; and axially flexible means for attaching the opposite end of said air delivery tube to said support flange; and said fuel delivery tube and said air delivery tube define cooperatively engaging members generally adjacent their one end so that when said engagement is effected said nozzle is seated in said opening in a substantially sealed engagement therebetween and wherein, said flexible means mounting said air delivery tube to said support flange accommodates, through axial deflection, variations in the axial expansion of said two tubes.

Claim 3

The fuel nozzle assembly of claim 1 wherein said engaging members comprise a plurality of tab members extending from the facing surfaces of said respective tubes and having engaging camming surfaces whereby relative rotation of the tubes in one direction forces the nozzle into sealing engagement within the opening in said air delivery tube.

Claim 4

A fuel assembly of claim 1 wherein said axially flexible mounting means comprises a generally thin-walled ring member, having an outer periphery securely attached to said support flange and an inner periphery attached to said air delivery tube wherein axial dimensional changes of said air delivery tube cause said ring to deflect axially.

Claim 5

Structure according to claim 3 wherein said air delivery tube including said wall comprises a unitary member whereby the desired orientation of said apertures in said wall as mounted in said gas turbine engine can be maintained.

Claim 6

Structure according to claim 1 wherein said fuel inlet means on said fuel delivery tube comprises a collar member attached to said opposite end of said fuel delivery tube and having an opening therethrough in communication with said tube and wherein said collar member is disposed in a counter-sunk area on one face of said support flange to axially locate said tube with respect to said flange.

Claim 7

Structure according to claim 5 wherein said air delivery tube is stationarily mounted with respect to rotation to said support flange and said fuel delivery tube is removably supported on said support flange; and wherein said engagement between said air delivery tube and said fuel delivery tube is effected by rotation of said fuel tube relative to said stationary flange and air tube and whereby reverse rotation permits withdrawal of said fuel tube for ready access to said air tube.

Claim 8

A fuel nozzle assembly for a gas turbine engine comprising: a fuel nozzle tip having a frusto-conical surface and a threaded skirt portion; an elongated fuel delivery tube having one end engaging the nozzle tip and the opposite end defining an enlarged collar member; a support flange having an axial opening therethrough and means on one face for mounting the collar member; an air delivery tube encircling said fuel delivery tube in spaced relation to define an annular air passage therebetween, said air delivery tube terminating at one end in a wall defining a frusto-conical opening for sealing engagement with the frusto-conical surface of the nozzle tip, said wall defining apertures therethrough for atomizing air exit ports, and means for mounting the opposite end of said delivery tube to said support flange; said fuel delivery tube and said air delivery tube defining tab members providing a breech-lock engagement therebetween with said members disposed adjacent the end of said fuel delivery tube mounting said nozzle tip, and wherein said nozzle is seated in said frusto-conical opening in a substantially sealed relationship when said breech-lock engagement is completed; and further, wherein said means for mounting said air delivery tube to said support flange is generally axially flexible to accommodate, through deflection, variations in the axial expansion of said two tubes due to any differential in temperatures to which they are exposed and permitting the continuous sealed engagement between said frusto-conical surfaces and opening.

Claim 9

A fuel nozzle assembly for a gas turbine engine comprising: a fuel nozzle tip having a frusto-conical surface and a threaded skirt portion; an elongated fuel delivery tube having one end engaging the nozzle tip and the opposite end defining an enlarged collar member; a support flange having an axial opening therethrough and means on one face for mounting the collar member; an air delivery tube encircling said fuel delivery tube in spaced relation to define an annular air passage therebetween, said air delivery tube terminating at one end in a wall defining a frusto-conical opening for sealing engagement with the frusto-conical surface of the nozzle tip, said wall defining apertures therethrough for atomizing air exit ports, and means for mounting the opposite end of said delivery tube to said support flange; said fuel delivery tube and said air delivery tube defining tab members providing a breech-lock engagement therebetween with said members disposed adjacent the end of said fuel delivery tube mounting said nozzle tip, and wherein said nozzle is seated in said frusto-conical opening in a substantially sealed relationship when said breech-lock engagement is completed; and further, wherein said means for mounting said air delivery tube to said support flange is generally axially flexible to accommodate, through deflection, variations in the axial expansion of said two tubes due to any differential in temperatures to which they are exposed and permitting the continuous sealed engagement between said frusto-conical surfaces and opening.