Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirl assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

BACKGROUND

The present disclosure relates to a gas turbine engine and, more particularly, to a swirler therefor.

Gas turbine engines, such as those that power modern commercial and military aircraft, include a compressor to pressurize airflow, a combustor to burn a hydrocarbon fuel in the presence of the pressurized airflow, and a turbine to extract energy from the resultant combustion gases.

The combustor generally includes radially spaced inner and outer liners that define an annular combustion chamber therebetween. Arrays of circumferentially distributed combustion air holes penetrate multiple axial locations along each liner to radially admit the pressurized air into the combustion chamber. A plurality of circumferentially distributed fuel nozzles project into a forward section of the combustion chamber through a respective fuel nozzle swirler to supply the fuel to be mixed with the pressurized air.

SUMMARY

A swirler body for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an annular mount face which defines at least one pocket.

In a further embodiment of the foregoing embodiment, the swirler body includes a first slot and a second slot which are generally radial with respect to a centerline of said swirler body, the at least one pocket between the first slot and the second slot.

In a further embodiment of any of the foregoing embodiments, the at least one pocket extends through an outer surface of the swirler body.

A swirler assembly for a combustor of a gas turbine engine according to another disclosed non-limiting embodiment of the present disclosure includes a swirler first body with an annular first mount face which defines at least one first pocket, and a swirler second body with a second annular mount face which abuts the annular first mount face, the second annular mount face defines at least one second pocket.

In a further embodiment of any of the foregoing embodiments, the swirler first body includes a first slot and a second slot which are generally radial with respect to a centerline of said swirler first body, the at least one pocket between the first slot and the second slot. In the alternative or additionally thereto, the swirler second body includes a first slot and a second slot which are generally radial with respect to a centerline of said swirler second body, the at least one pocket between the first slot and the second slot.

In the alternative or additionally thereto, the outer surface is cylindrical.

In a further embodiment of any of the foregoing embodiments, a guide housing is mounted to the swirler first body.

In the alternative or additionally thereto, the nozzle guide is mounted to the guide housing.

In the alternative or additionally thereto, a capture plate is mounted to the guide housing to retain the nozzle guide, the nozzle guide movable with respect to the guide housing.

In the alternative or additionally thereto, a capture plate is mounted to the guide housing to retain the nozzle guide.

In the alternative or additionally thereto, the capture plate is annular.

In the alternative or additionally thereto, the capture plate includes a non-circular inner periphery.

In the alternative or additionally thereto, the capture plate includes a scalloped inner periphery.

A method of lightening a swirler assembly for a combustor of a gas turbine engine according to another disclosed non-limiting embodiment of the present disclosure includes at least one pocket within an annular mount face of a swirler body.

In a further embodiment of the foregoing embodiment, the method includes defining at least one pocket completely within the annular mount face.

In a further embodiment of any of the foregoing embodiments, the method includes defining at least one pocket adjacent to a slot.

In a further embodiment of any of the foregoing embodiments, the method includes at least one pocket through an outer surface of the swirler body.

In a further embodiment of any of the foregoing embodiments, the method includes defining at least one pocket adjacent to a second pocket in a swirler second body.

DETAILED DESCRIPTION

FIG. 1schematically illustrates a gas turbine engine20. The gas turbine engine20is disclosed herein as a two-spool turbofan that generally incorporates a fan section22, a compressor section24, a combustor section26and a turbine section28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section22drives air along a bypass flowpath while the compressor section24drives air along a core flowpath for compression and communication into the combustor section26then expansion through the turbine section28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines such as a three-spool (plus fan) engine wherein an intermediate spool includes an intermediate pressure compressor (IPC) between the LPC and HPC and an intermediate pressure turbine (IPT) between the HPT and LPT.

The engine20generally includes a low spool30and a high spool32mounted for rotation about an engine central longitudinal axis A relative to an engine static structure36via several bearing structures38. The low spool30generally includes an inner shaft40that interconnects a fan42, a low pressure compressor44(“LPC”) and a low pressure turbine46(“LPT”). The inner shaft40drives the fan42directly or through a geared architecture48to drive the fan42at a lower speed than the low spool30. An exemplary reduction transmission is an epicyclic transmission, namely a planetary or star gear system.

The high spool32includes an outer shaft50that interconnects a high pressure compressor52(“HPC”) and high pressure turbine54(“HPT”). A combustor56is arranged between the high pressure compressor52and the high pressure turbine54. The inner shaft40and the outer shaft50are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes.

Core airflow is compressed by the low pressure compressor44then the high pressure compressor52, mixed with the fuel and burned in the combustor56, then expanded over the high pressure turbine54and low pressure turbine46. The turbines54,46rotationally drive the respective low spool30and high spool32in response to the expansion.

The main engine shafts40,50are supported at a plurality of points by bearing structures38within the static structure36. It should be understood that various bearing structures38at various locations may alternatively or additionally be provided.

With reference toFIG. 2, the combustor56generally includes a combustor outer wall60and a combustor inner wall62. The outer wall60and the inner wall62are spaced inward from a diffuser case64such that a chamber66is defined therebetween. The chamber66is generally annular in shape and is defined between combustor walls60,62.

The outer wall60and the diffuser case64define an annular outer plenum76and the inner wall62and the diffuser case64define an annular inner plenum78. It should be understood that although a particular combustor is illustrated, other combustor types with various combustor liner arrangements will also benefit herefrom. It should be further understood that the disclosed cooling flow paths are but an illustrated embodiment and should not be limited only thereto.

Each wall60,62generally includes a respective support shell68,70that supports one or more respective liners72,74mounted to a hot side of the respective support shell68,70. The liners72,74define a liner array that may be generally annular in shape. Each of the liners72,74may be generally rectilinear and manufactured of, for example, a nickel based super alloy or ceramic material.

The combustor56further includes a forward assembly80immediately downstream of the compressor section24to receive compressed airflow therefrom. The forward assembly80generally includes an annular hood82, a bulkhead subassembly84, a multiple of fuel nozzles86(one shown) and a multiple of swirlers90(one shown) that defines a central opening92. The annular hood82extends radially between, and is secured to, the forwardmost ends of the walls60,62. The annular hood82includes a multiple of circumferentially distributed hood ports94that accommodate the respective fuel nozzle86and introduce air into the forward end of the chamber66. The centerline of the fuel nozzle86is concurrent with the centerline F of the respective swirler90. Each fuel nozzle86may be secured to the diffuser case64to project through one of the hood ports94and through the central opening92within the respective swirler90.

Each swirler90is circumferentially aligned with one of the hood ports94to project through the bulkhead subassembly84. Each bulkhead subassembly84includes a bulkhead support shell96secured to the walls60,62, and a multiple of circumferentially distributed bulkhead heatshields98secured to the bulkhead support shell96around the central opening92.

The forward assembly80directs a portion of the core airflow into the forward end of the chamber66while the remainder enters the annular outer plenum76and the annular inner plenum78. The multiple of fuel nozzles86, swirler90and surrounding structure generate a swirling, intimately blended fuel-air mixture that supports combustion in the chamber66.

With reference toFIG. 3, each of the swirlers90generally includes a capture plate100, a nozzle guide102, a guide housing104, a swirler first body106and a swirler second body108. The capture plate100is mounted to the guide housing104to retain the nozzle guide102, the nozzle guide102is movable with respect to the guide housing104. It should be appreciated that any number of swirler bodies as well as alternative or additional components may be utilized herewith and that the two part swirler body shown is merely but one example assembly.

With reference toFIG. 4, the swirler first body106generally includes a base section110and a frustoconical section112which extends downstream of the base section110. The base section110includes a multiple of legs114defined by a multiple of slots116opposite the frustoconical section112. The slots116are generally radial with respect to the centerline F to receive primary combustion core airflow from within the bulkhead support shell96toward the fuel nozzle86within the chamber66for combustion (FIG. 5). It should be appreciated that generally radial as defined herein means transverse to said centerline F but may include an angled component to impart a swirl to the primary combustion core airflow about the centerline F.

A multiple of pockets118are formed in and communicate axially through the base section110opposite the legs114. The multiple of pockets118in the disclosed non-limiting embodiment are completely contained within a mount face120which abuts the swirler second body108(FIG. 5).

With reference toFIG. 6, the swirler second body108generally includes a base section122and a frustoconical section124which extends downstream of the base section122. The base section122includes a multiple of slots126and a multiple of pockets128in a mount face130of the swirler second body108. The multiple of slots126are generally radial with respect to the centerline F to receive primary combustion core airflow to be communicated toward the chamber66for combustion from within the bulkhead support shell96toward the fuel nozzle86. The multiple of slots126may provide counter swirl with respect to slots116(FIG. 4).

The mount face130of the swirler second body108abuts the mount face120of the swirler first body106such that the pockets118,128may be in axial association but are not exposed to the primary combustion core airflow (FIG. 7). That is, the pockets118,128form respective single hollow areas contained within the mount faces120,130.

The base section122at least partially overlaps the base section110to seal as well as rotationally locate the swirler first and second bodies106,108. That is, a lip of the base section122may at least partially surround the base section110.

The pockets118,128thereby reduce the weight of the swirler90. It should be appreciated that the pockets118,128may be machined or otherwise formed into a cast component or formed directly through, for example only, Direct Laser Metal Sintering (DLMS).

With reference toFIG. 8, the capture plate100may also be lightened through formation of a scalloped inner aperture100A. It should be appreciated that the scalloping is but one disclosed non-limiting embodiment and various geometries for the inner aperture may be provided such as rectilinear, oval or other non-circular shapes. In the disclosed non-limiting embodiment, each swirler90has been lightened by approximately 0.04 pounds (18 grams) which, for example only, in a combustor with eighteen swirlers provides a 0.7 pound (317 gram) weight savings.

With reference toFIGS. 11A-11B, in another disclosed, non-limiting embodiment, a swirler90″ includes a swirler second body108′ in which the pockets128′ extend through an outer surface132such that primary combustion core airflow may enter the pockets128′ and pockets118but is trapped therein. That is, the primary combustion core airflow may impinge within the pockets128′,118but is not swirled nor communicated toward the combustion chamber66for combustion.

Referring toFIG. 9(swirler90′) andFIGS. 11A-11B, in some embodiments the pockets128′ are located between each of the multiple of slots126′ such that relatively thin legs134are defined, each of which includes one of the multiple of slots126′ which communicate primary combustion core airflow toward the combustion chamber66for combustion. At least one of the multiple of legs134A may be of an extended length to be received within a corresponding axial recess136in the swirler first body106′ to assure the swirler first body106′ is properly clocked relative to the swirler second body108′ (FIG. 10). In other words, the pockets118,128are aligned in some manner so as to be sealed off from the primary airflow through the swirler. The pockets118,128do not necessarily have to be aligned one to another so long as there is no interaction with the primary airflow. The clocking feature provides alignment to ensure the swirler first body106′ is properly clocked relative to the swirler second body108′ and can't be misaligned during an assembly process. It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.