Abstract:
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 swirler 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.

Description:
[0001]    This application is a continuation of U.S. patent application Ser. No. 13/614,657 filed Sep. 13, 2012, the contents of which are incorporated herein by reference. 
       BACKGROUND 
       [0002]    The present disclosure relates to a gas turbine engine and, more particularly, to a swirler therefor. 
         [0003]    Gas turbine engines, such as those that power modem commercial and military aircraft, include a compressor to pressurize airflow, a combustor to bum a hydrocarbon fuel in the presence of the pressurized airflow, and a turbine to extract energy from the resultant combustion gases. 
         [0004]    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 
       [0005]    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. 
         [0006]    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. 
         [0007]    In a further embodiment of any of the foregoing embodiments, the at least one pocket extends through an outer surface of the swirler body. 
         [0008]    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. 
         [0009]    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. 
         [0010]    In the alternative or additionally thereto, the outer surface is cylindrical. 
         [0011]    In a further embodiment of any of the foregoing embodiments, a guide housing is mounted to the swirler first body. 
         [0012]    In the alternative or additionally thereto, the nozzle guide is mounted to the guide housing. 
         [0013]    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. 
         [0014]    In the alternative or additionally thereto, a capture plate is mounted to the guide housing to retain the nozzle guide. 
         [0015]    In the alternative or additionally thereto, the capture plate is annular. 
         [0016]    In the alternative or additionally thereto, the capture plate includes a non-circular inner periphery. 
         [0017]    In the alternative or additionally thereto, the capture plate includes a scalloped inner periphery. 
         [0018]    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. 
         [0019]    In a further embodiment of the foregoing embodiment, the method includes defining at least one pocket completely within the annular mount face. 
         [0020]    In a further embodiment of any of the foregoing embodiments, the method includes defining at least one pocket adjacent to a slot. 
         [0021]    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. 
         [0022]    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. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0023]    Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows: 
           [0024]      FIG. 1  is a schematic cross-section of a gas turbine engine; 
           [0025]      FIG. 2  is a partial sectional view of an exemplary annular combustor that may be used with the gas turbine engine shown in  FIG. 1 ; 
           [0026]      FIG. 3  is an exploded view of a swirler assembly according to one non-limiting embodiment; 
           [0027]      FIG. 4  is an expanded view of a swirler first body; 
           [0028]      FIG. 5  is a partial sectional view of the swirler assembly of  FIG. 3 ; 
           [0029]      FIG. 6  is an expanded view of a swirler second body; 
           [0030]      FIG. 7  is an expanded partial sectional view of the swirler assembly of  FIG. 3 ; 
           [0031]      FIG. 8  is an end view of the swirler assembly of  FIG. 3 ; 
           [0032]      FIG. 9  is an exploded view of a swirler assembly according to another non-limiting embodiment; and 
           [0033]      FIG. 10  is an expanded perspective view of the swirler assembly of  FIG. 9 . 
           [0034]      FIGS. 11A-11B  illustrate an exploded view of a swirler assembly according to another non-limiting embodiment. 
       
    
    
     DETAILED DESCRIPTION 
       [0035]      FIG. 1  schematically illustrates a gas turbine engine  20 . The gas turbine engine  20  is disclosed herein as a two-spool turbofan that generally incorporates a fan section  22 , a compressor section  24 , a combustor section  26  and a turbine section  28 . Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section  22  drives air along a bypass flowpath while the compressor section  24  drives air along a core flowpath for compression and communication into the combustor section  26  then expansion through the turbine section  28 . 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. 
         [0036]    The engine  20  generally includes a low spool  30  and a high spool  32  mounted for rotation about an engine central longitudinal axis A relative to an engine static structure  36  via several bearing structures  38 . The low spool  30  generally includes an inner shaft  40  that interconnects a fan  42 , a low pressure compressor  44  (“LPC”) and a low pressure turbine  46  (“LPT”). The inner shaft  40  drives the fan  42  directly or through a geared architecture  48  to drive the fan  42  at a lower speed than the low spool  30 . An exemplary reduction transmission is an epicyclic transmission, namely a planetary or star gear system. 
         [0037]    The high spool  32  includes an outer shaft  50  that interconnects a high pressure compressor  52  (“HPC”) and high pressure turbine  54  (“HPT”). A combustor  56  is arranged between the high pressure compressor  52  and the high pressure turbine  54 . The inner shaft  40  and the outer shaft  50  are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes. 
         [0038]    Core airflow is compressed by the low pressure compressor  44  then the high pressure compressor  52 , mixed with the fuel and burned in the combustor  56 , then expanded over the high pressure turbine  54  and low pressure turbine  46 . The turbines  54 ,  46  rotationally drive the respective low spool  30  and high spool  32  in response to the expansion. 
         [0039]    The main engine shafts  40 ,  50  are supported at a plurality of points by bearing structures  38  within the static structure  36 . It should be understood that various bearing structures  38  at various locations may alternatively or additionally be provided. 
         [0040]    With reference to  FIG. 2 , the combustor  56  generally includes a combustor outer wall  60  and a combustor inner wall  62 . The outer wall  60  and the inner wall  62  are spaced inward from a diffuser case  64  such that a chamber  66  is defined therebetween. The chamber  66  is generally annular in shape and is defined between combustor walls  60 ,  62 . 
         [0041]    The outer wall  60  and the diffuser case  64  define an annular outer plenum  76  and the inner wall  62  and the diffuser case  64  define an annular inner plenum  78 . 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. 
         [0042]    Each wall  60 ,  62  generally includes a respective support shell  68 ,  70  that supports one or more respective liners  72 ,  74  mounted to a hot side of the respective support shell  68 ,  70 . The liners  72 ,  74  define a liner array that may be generally annular in shape. Each of the liners  72 ,  74  may be generally rectilinear and manufactured of, for example, a nickel based super alloy or ceramic material. 
         [0043]    The combustor  56  further includes a forward assembly  80  immediately downstream of the compressor section  24  to receive compressed airflow therefrom. The forward assembly  80  generally includes an annular hood  82 , a bulkhead subassembly  84 , a multiple of fuel nozzles  86  (one shown) and a multiple of swirlers  90  (one shown) that defines a central opening  92 . The annular hood  82  extends radially between, and is secured to, the forwardmost ends of the walls  60 ,  62 . The annular hood  82  includes a multiple of circumferentially distributed hood ports  94  that accommodate the respective fuel nozzle  86  and introduce air into the forward end of the chamber  66 . The centerline of the fuel nozzle  86  is concurrent with the centerline F of the respective swirler  90 . Each fuel nozzle  86  may be secured to the diffuser case  64  to project through one of the hood ports  94  and through the central opening  92  within the respective swirler  90 . 
         [0044]    Each swirler  90  is circumferentially aligned with one of the hood ports  94  to project through the bulkhead subassembly  84 . Each bulkhead subassembly  84  includes a bulkhead support shell  96  secured to the walls  60 ,  62 , and a multiple of circumferentially distributed bulkhead heatshields  98  secured to the bulkhead support shell  96  around the central opening  92 . 
         [0045]    The forward assembly  80  directs a portion of the core airflow into the forward end of the chamber  66  while the remainder enters the annular outer plenum  76  and the annular inner plenum  78 . The multiple of fuel nozzles  86 , swirler  90  and surrounding structure generate a swirling, intimately blended fuel-air mixture that supports combustion in the chamber  66 . 
         [0046]    With reference to  FIG. 3 , each of the swirlers  90  generally includes a capture plate  100 , a nozzle guide  102 , a guide housing  104 , a swirler first body  106  and a swirler second body  108 . The capture plate  100  is mounted to the guide housing  104  to retain the nozzle guide  102 , the nozzle guide  102  is movable with respect to the guide housing  104 . 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. 
         [0047]    With reference to  FIG. 4 , the swirler first body  106  generally includes a base section  110  and a frustoconical section  112  which extends downstream of the base section  110 . The base section  110  includes a multiple of legs  114  defined by a multiple of slots  116  opposite the frustoconical section  112 . The slots  116  are generally radial with respect to the centerline F to receive primary combustion core airflow from within the bulkhead support shell  96  toward the fuel nozzle  86  within the chamber  66  for 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. 
         [0048]    A multiple of pockets  118  are folioed in and communicate axially through the base section  110  opposite the legs  114 . The multiple of pockets  118  in the disclosed non-limiting embodiment are completely contained within a mount face  120  which abuts the swirler second body  108  ( FIG. 5 ). 
         [0049]    With reference to  FIG. 6 , the swirler second body  108  generally includes a base section  122  and a frustoconical section  124  which extends downstream of the base section  122 . The base section  122  includes a multiple of slots  126  and a multiple of pockets  128  in a mount face  130  of the swirler second body  108 . The multiple of slots  126  are generally radial with respect to the centerline F to receive primary combustion core airflow to be communicated toward the chamber  66  for combustion from within the bulkhead support shell  96  toward the fuel nozzle  86 . The multiple of slots  126  may provide counter swirl with respect to slots  116  ( FIG. 4 ). 
         [0050]    The mount face  130  of the swirler second body  108  abuts the mount face  120  of the swirler first body  106  such that the pockets  118 ,  128  may be in axial association but are not exposed to the primary combustion core airflow ( FIG. 7 ). That is, the pockets  118 ,  128  form respective single hollow areas contained within the mount faces  120 ,  130 . 
         [0051]    The base section  122  at least partially overlaps the base section  110  to seal as well as rotationally locate the swirler first and second bodies  106 ,  108 . That is, a lip of the base section  122  may at least partially surround the base section  110 . 
         [0052]    The pockets  118 ,  128  thereby reduce the weight of the swirler  90 . It should be appreciated that the pockets  118 ,  128  may be machined or otherwise framed into a cast component or formed directly through, for example only, Direct Laser Metal Sintering (DLMS). 
         [0053]    With reference to  FIG. 8 , the capture plate  100  may also be lightened through formation of a scalloped inner aperture  100 A. 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 swirler  90  has 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. 
         [0054]    With reference to  FIGS. 11A-11B , in another disclosed, non-limiting embodiment, a swirler  90 ″ includes a swirler second body  108 ′ in which the pockets  128 ′ extend through an outer surface  132  such that primary combustion core airflow may enter the pockets  128 ′ and pockets  118  but is trapped therein. That is, the primary combustion core airflow may impinge within the pockets  128 ′,  118  but is not swirled nor communicated toward the combustion chamber  66  for combustion. 
         [0055]    Referring to  FIGS. 9  (swirler  90 ′) and  FIGS. 11A-11B , in some embodiments the pockets  128 ′ are located between each of the multiple of slots  126 ′ such that relatively thin legs  134  are defined, each of which includes one of the multiple of slots  126 ′ which communicate primary combustion core airflow toward the combustion chamber  66  for combustion. At least one of the multiple of legs  134 A may be of an extended length to be received within a corresponding axial recess  136  in the swirler first body  106 ′ to assure the swirler first body  106 ′ is properly clocked relative to the swirler second body  108 ′ ( FIG. 10 ). In other words, the pockets  118 ,  128  are aligned in some manner so as to be sealed off from the primary airflow through the swirler. The pockets  118 ,  128  do 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 body  106 ′ is properly clocked relative to the swirler second body  108 ′ and can&#39;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 noimal operational attitude of the vehicle and should not be considered otherwise limiting. 
         [0056]    It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom. 
         [0057]    Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present disclosure. 
         [0058]    The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the disclosure may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.