Patent Publication Number: US-11047575-B2

Title: Combustor heat shield panel

Description:
BACKGROUND 
     The subject matter disclosed herein generally relates to gas turbine engines and, more particularly, to a method and apparatus for mitigating heat in cooling surfaces of gas turbine engines using heat shield panels. 
     In one example, a combustor of a gas turbine engine may be configured to burn fuel in a combustion area. Such configurations may place substantial heat load on the structure of the combustor (e.g., heat shield panels, shells, etc.). Such heat loads may dictate that special consideration is given to structures, which may be configured as heat shields or panels, and to the cooling of such structures to protect these structures. Excess temperatures at these structures may lead to oxidation, cracking, and high thermal stresses of the heat shields panels. 
     SUMMARY 
     According to an embodiment, a combustor for use in a gas turbine engine is provided. The combustor enclosing a combustion chamber having a combustion area, wherein the combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked heat shield panel is parallel to the shell. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the combustor includes a first section and a second section, wherein the kink of the shell is a junction of a first section of the combustor having a first coned shape and the second section of the combustor having a second coned shape. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kink of the shell is a point in the shell at which the cross sectional area of the combustor changes. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the shell further includes an inner surface, an outer surface opposite the inner surface, and a mounting orifice extending through the shell from the inner surface to the outer surface, the mounting orifice being located proximate the kink of the shell. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the mounting orifice is located at or on the kink of the shell. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the mounting stud is located at or on the kink of the kinked heat shield panel. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the shell further includes an inner surface, an outer surface opposite the inner surface, and a mounting orifice extending through the shell from the inner surface to the outer surface, the mounting orifice being located proximate the kink of the shell, and wherein the mounting orifice is located opposite the mounting stud. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked heat shield panel further includes a forward edge, a rearward edge opposite the forward edge, a first lateral edge, and a second lateral edge opposite the first lateral edge, wherein the first lateral edge and the second lateral edge extend from the forward edge to the rearward edge, and wherein the kink of the kinked heat shield panel extends from the first lateral edge to the second lateral edge. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kink of the kinked heat shield panel extends from the first lateral edge to the second lateral edge about parallel to at least one of the forward edge and the rearward edge. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked heat shield panel further includes a locating pin located proximate the mounting stud and extending away from the second surface, wherein the locating pin further includes a platform surface operably shaped to conform to the inner surface of the shell opposite the locating pin. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include: a nut secured to the mounting stud; and a kinked washer interposed between the nut and the outer surface of the shell, the kinked washer being operably shaped to conform to the outer surface of the shell proximate the kink of the shell. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked washer further includes a first surface proximate the outer surface of the shell and a second surface opposite the first surface, the second surface being proximate the nut, and wherein the first surface of the kinked washer is operably shaped to conform to the outer surface of the shell proximate the kink of the shell. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the second surface of the kinked washer is operably shaped to conform to the nut. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked washer further includes a receiving orifice extending through the kinked washer from the first surface to the second surface, the mounting stud being located within the kinked orifice. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the mounting orifice is circular, oval or slotted in shape. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface, and wherein the mounting stud is located proximate at least one of the first lateral edge and the second lateral edge. 
     In addition to one or more of the features described above, or as an alternative, further embodiments may include that the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface, and wherein the mounting stud is centered between the first lateral edge and the second lateral edge. 
     According to another embodiment, a kinked heat shield panel for use in a combustor of a gas turbine engine is provided. The kinked heat shield panel including: a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface; and a forward edge, a rearward edge opposite the forward edge, a first lateral edge, and a second lateral edge opposite the first lateral edge, wherein the first lateral edge and the second lateral edge extend from the forward edge to the rearward edge, and wherein the kink of the kinked heat shield panel extends from the first lateral edge to the second lateral edge. 
     The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, that the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting. 
    
    
     
       BRIEF DESCRIPTION 
       The following descriptions should not be considered limiting in any way. With reference to the accompanying drawings, like elements are numbered alike: 
         FIG. 1  is a partial cross-sectional illustration of a gas turbine engine; 
         FIG. 2  is a cross-sectional illustration of a combustor; 
         FIG. 3  is an enlarged view of a kink in a shell of the combustor of  FIG. 2 ; 
         FIG. 4  is a view of a kinked heat shield panel and a shell for use in the combustor of  FIG. 2 , in accordance with an embodiment of the present disclosure; 
         FIG. 5  is a cross-sectional view of the kinked heat shield panel, the shell, a kinked washer, and a nut, in accordance with an embodiment of the present disclosure; 
         FIG. 6  is a top view of the kinked heat shield panel of  FIGS. 4 and 5 , in accordance with an embodiment of the present disclosure; and 
         FIG. 7  is a top view of the shell of  FIGS. 4 and 5 , in accordance with an embodiment of the present disclosure. 
     
    
    
     The detailed description explains embodiments of the present disclosure, together with advantages and features, by way of example with reference to the drawings. 
     DETAILED DESCRIPTION 
     A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures. 
       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 flow path B in a bypass duct, while the compressor section  24  drives air along a core flow path C for compression and communication into the combustor section  26  then expansion through the turbine section  28 . Although depicted as a two-spool 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 two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. 
     The exemplary engine  20  generally includes a low speed spool  30  and a high speed spool  32  mounted for rotation about an engine central longitudinal axis A relative to an engine static structure  36  via several bearing systems  38 . It should be understood that various bearing systems  38  at various locations may alternatively or additionally be provided, and the location of bearing systems  38  may be varied as appropriate to the application. 
     The low speed spool  30  generally includes an inner shaft  40  that interconnects a fan  42 , a low pressure compressor  44  and a low pressure turbine  46 . The inner shaft  40  is connected to the fan  42  through a speed change mechanism, which in exemplary gas turbine engine  20  is illustrated as a geared architecture  48  to drive the fan  42  at a lower speed than the low speed spool  30 . The high speed spool  32  includes an outer shaft  50  that interconnects a high pressure compressor  52  and high pressure turbine  54 . A combustor  300  is arranged in exemplary gas turbine  20  between the high pressure compressor  52  and the high pressure turbine  54 . An engine static structure  36  is arranged generally between the high pressure turbine  54  and the low pressure turbine  46 . The engine static structure  36  further supports bearing systems  38  in the turbine section  28 . The inner shaft  40  and the outer shaft  50  are concentric and rotate via bearing systems  38  about the engine central longitudinal axis A which is collinear with their longitudinal axes. 
     The core airflow is compressed by the low pressure compressor  44  then the high pressure compressor  52 , mixed and burned with fuel in the combustor  300 , then expanded over the high pressure turbine  54  and low pressure turbine  46 . The turbines  46 ,  54  rotationally drive the respective low speed spool  30  and high speed spool  32  in response to the expansion. It will be appreciated that each of the positions of the fan section  22 , compressor section  24 , combustor section  26 , turbine section  28 , and fan drive gear system  48  may be varied. For example, gear system  48  may be located aft of combustor section  26  or even aft of turbine section  28 , and fan section  22  may be positioned forward or aft of the location of gear system  48 . 
     The engine  20  in one example is a high-bypass geared aircraft engine. In a further example, the engine  20  bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), the geared architecture  48  is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine  46  has a pressure ratio that is greater than about five. In one disclosed embodiment, the engine  20  bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor  44 , and the low pressure turbine  46  has a pressure ratio that is greater than about five 5:1. Low pressure turbine  46  pressure ratio is pressure measured prior to inlet of low pressure turbine  46  as related to the pressure at the outlet of the low pressure turbine  46  prior to an exhaust nozzle. The geared architecture  48  may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans. 
     A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section  22  of the engine  20  is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,688 meters). The flight condition of 0.8 Mach and 35,000 ft (10,688 meters), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] 0.5 . The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 m/sec). 
     Referring now to  FIG. 2  and with continued reference to  FIG. 1 , the combustor section  26  of the gas turbine engine  20  is shown. The combustor  300  of  FIG. 2  is an impingement film float wall combustor. It is understood that while an impingement film float wall combustor is utilized for exemplary illustration, the embodiments disclosed herein may be applicable to other types of combustors for gas turbine engines including but not limited to double pass liner combustors and float wall combustors. As illustrated, a combustor  300  defines a combustion chamber  302 . The combustion chamber  302  includes a combustion area  370  within the combustion chamber  302 . The combustor  300  includes an inlet  306  and an outlet  308  through which air may pass. The air may be supplied to the combustor  300  by a pre-diffuser  110 . Air may also enter the combustion chamber  302  through other holes in the combustor  300  including but not limited to quench holes  310 , as seen in  FIG. 2 . 
     Compressor air is supplied from the compressor section  24  into a pre-diffuser  110 , which then directs the airflow toward the combustor  300 . The combustor  300  and the pre-diffuser  110  are separated by a dump region  113  from which the flow separates into an inner shroud  114  and an outer shroud  116 . As air enters the dump region  113 , a portion of the air may flow into the combustor inlet  306 , a portion may flow into the inner shroud  114 , and a portion may flow into the outer shroud  116 . 
     The air from the inner shroud  114  and the outer shroud  116  may then enter the combustion chamber  302  by means of one or more impingement holes  307  in the shell  600  and one or more secondary apertures  309  in the heat shield panels  400 . The impingement holes  307  and secondary apertures  309  may include nozzles, holes, etc. The air may then exit the combustion chamber  302  through the combustor outlet  308 . At the same time, fuel may be supplied into the combustion chamber  302  from a fuel injector  320  and a pilot nozzle  322 , which may be ignited within the combustion chamber  302 . The combustor  300  of the engine combustion section  26  may be housed within diffuser cases  124  which may define the inner shroud  114  and the outer shroud  116 . 
     The combustor  300 , as shown in  FIG. 2 , includes multiple heat shield panels  400  that are attached to one or more shells  600  (See  FIG. 3 ). The heat shield panels  400  may be arranged parallel to the shell  600 . The shell  600  includes a radially inward shell  600   a  and a radially outward shell  600   b  in a facing spaced relationship defining the combustion chamber  300  therebetween. The shell  600  also includes a forward shell  600   c  extending between the radially inward shell  600   a  and the radially outward shell  600   b . The forward shell  600   c  further bounds the combustion chamber  300  on a forward end. The radially inward shell  600   a  and the radially outward shell  600   b  extend circumferentially around the longitudinal engine axis A. The radial inward shell  600   a  is located radially inward from the radially outward shell  600   b.    
     The heat shield panels  400  can be removably mounted to the shell  600  by one or more attachment mechanisms  332 . In some embodiments, the attachment mechanism  332  may be integrally formed with a respective heat shield panel  400 , although other configurations are possible. In some embodiments, the attachment mechanism  332  may be a threaded mounting stud or other structure that may extend from the respective heat shield panel  400  through the interior surface to a receiving portion or aperture of the shell  600  such that the heat shield panel  400  may be attached to the shell  600  and held in place. The heat shield panels  400  partially enclose a combustion area  370  within the combustion chamber  302  of the combustor  300 . 
     Referring now to  FIGS. 2 and 3 , with continued reference to  FIG. 1 , a kink  500  in the shell  600  is illustrated, in accordance with an embodiment of the present disclosure. For example, the kink  500  may be a bend in the shell  600 . The kink  500  is present in the radially inward shell  600   a  and the radially outward shell  600   b  in order to meet the volume and length requirement of combustor  300 . The kink  500  is a junction of a first section  330   a  of the combustor  300  having a first coned shape and a second section  300   b  of the combustor  300  having a second coned shape. The first coned shape of the first section  300   a  is different from the second coned shape of the second section  300   b , as shown in  FIG. 3 . The kink  500  is a point in the shell  600  at which the cross sectional area of the combustor  300  changes. Conventionally, as shown in  FIG. 3  the nature of the kink  500  compels that there be two separate heat shield panels  400   a ,  400   b  forward and aft of the kink  500 , as such there is a gap  502  formed between the two separate heat shield panels  400   a ,  400   b . The kink  500  and the gap  502  extends circumferentially around the combustor  300 . The gap  502  is located between a first heat shield panel  400   a  and a second heat shield panel  400   b . The first heat shield panel  400   a  may be located forward of the gap  502  and the second heat shield panel  400   b  may be located aft gap  502 . The gap  502  exposes an inner surface  610  of the shell  600  at the kink  500  to elevated temperatures within the combustion area  302 . Excessive heat in the shell  600  at the area of the gap  502  may lead to oxidation, cracking, and high thermal stresses of the shell  600 . Embodiments discussed herein seek to address this gap  502  proximate the kink  500  in the shell  600  by removing the gap  502  using a single kinked heat shield  400   c  (see  FIG. 4 ). 
     Referring now to  FIGS. 4 and 5 , with continued reference to  FIGS. 1-3 , a kinked heat shield panel  400   c  is illustrated, in accordance with an embodiment of the present disclosure. The kinked heat shield  400   c  may be used in place of both the first heat shield panel  400   a  and the second heat shield panel  400   b  of  FIG. 3 , thus advantageously reducing part count by replacing two components (e.g., the first heat shield panel  400   a  and the second heat shield panel  400   b ) with one component (e.g., kinked heat shield  400   c ) and also eliminating the gap  502  proximate the kink  500 . The kinked heat shield panel  400   c  includes a kink  700  located proximate the kink  500  of the shell  600 . The kink  700  of the kinked heat shield panel  400   c  may be in a facing space relationship with the kink  500  of the shell  600 . 
     The kinked heat shield panel  400   c  and the shell  600  are in a facing spaced relationship. The kinked heat shield panel  400   c  is about parallel to the shell  600 . The kinked heat shield panel  400   c  includes a first surface  410  oriented towards the combustion area  370  of the combustion chamber  302  and a second surface  420  opposite the first surface  410  oriented towards the shell  600 . The shell  600  has an inner surface  610  and an outer surface  620  opposite the inner surface  610 . The inner surface  610  is oriented toward the kinked heat shield panel  400   c . The outer surface  620  is oriented outward from the combustor  300  proximate the inner diameter branch  114  and the outer diameter branch  116 . 
     The kinked heat shield panel  400   c  may include one or more mounting studs  430  configured to attach the kinked heat shield panel  400   c  to the shell  600 . The mounting stud  430  extends outward away from the second surface  420  of the kinked heat shield panel  400   c . The shell  600  may include one or more mounting orifices  630  extending through the shell  600  from the inner surface  610  to the outer surface  620 . The mounting stud  430  is configured to extend through a mounting orifice  630  located opposite the mounting stud  430 . When the mounting stud  430  is inserted through the mounting orifice  630  the kinked heat shield panel  400   c  may be secured to the shell  600  via a nut  640  and a kinked washer  800 , as shown in  FIG. 5 . The nut  640  is configured to secure to the mounting stud  430 . For example, the nut  640  may twist onto the mounting stud  430  via a mating thread system, which is not shown for simplification of illustration. 
     The kinked heat shield panel  400   c  may include a mounting stud  430  located proximate the kink  700  of the kinked heat shield panel  400   c . The mounting stud  430  may be located at or on the kink  700  of the kinked heat shield panel  400   c , as shown in  FIG. 4 . The shell  600  may include a mounting orifice  630  located proximate the kink  500  of the shell  600 . The mounting orifice  630  may be located at or on the kink  500  of the shell  500 , as shown in  FIG. 4 . 
     The kinked heat shield panel  400   c  may include one or more locating pins  440  proximate the mounting stud  430  located proximate the kink  700  of the kinked heat shield panel  400   c . It is understood that mounting studs  430  not located proximate the kink  700  may also include locating pins. The locating pin  440  may be cylindrical in shape, as shown in  FIGS. 4 and 5 . The locating pin  440  includes a platform surface  442  operably shaped to conform to (i.e., match or mate flush with) the inner surface  610  of the shell  600  opposite the locating pin  440 . The locating pin  440  maintains the height of the impingement cavity  390  between the kinked heat shield panel  400   c  and the shell  600 . When the nut  640  is secured to the mounting stud  430  the kinked heat shield panel  400   c  is tightened and moves closer to the shell  600  until the inner surface  610  of the shell  600  sits flush with the platform surface  442  of the locating pin  440 . 
     The kinked washer  800  includes receiving orifice  830  configured to allow the mounting stud  430  to pass through the receiving orifice  830 . The kinked washer  800  includes a first surface  810  and a second surface  820  opposite the first surface  810 . The receiving orifice  830  extends through the kinked washer  800  from the first surface  810  to the second surface  820 . When assembled, the kinked washer  800  is located interposed between the nut  640  and the outer surface  620  of the shell  600 . When assembled, the mounting stud  430  is located within the receiving orifice  830 . The second surface  820  of the kinked washer  800  may be operably shaped to conform to (i.e., match or mate flush with) the nut  640 . The first surface  810  of the kinked washer  800  includes a kink  840 . The kink  840  in the first surface  810  of the kinked washer  800  is operably shaped to conform to (i.e., match or mate flush with) the outer surface  620  of the shell  600  at the kink  500  of the shell  600 . 
     Further, the first surface  810  may include a first portion  810   a  and a second portion  810   b . The first portion  810   a  may be located forward of the kink  840  and the second portion  810   b  may be located aft of the kink  840 , as shown in  FIG. 4 . The second surface  620  of the shell  600  may include a first portion  620   a  and a second portion  620   b . The first portion  620   a  may be located forward of the kink  500  and the second portion  620   b  may be located aft of the kink  500 , as shown in  FIG. 4 . The first portion  810   a  of the first surface  810  of the kinked washer  800  may be operably shaped to conform to (i.e., match or mate flush with) the first portion  620   a  of the second surface  620  of the shell  600  proximate the kink  500 . The second portion  810   b  of the first surface  810  of the kinked washer  800  may be operably shaped to conform to (i.e., match or mate flush with) the second portion  620   b  of the second surface  620  of the shell  600  proximate the kink  500 . 
     Referring now to  FIG. 6 , with continued reference to  FIGS. 1-5 , a top view of the kinked heat shield panel  400   c  is illustrated, in accordance with an embodiment of the present disclosure. The heat shield panel  400  is bounded on four sides by a forward edge  401   a , a rearward edge  401   b  opposite the forward edge  401   a , a first lateral edge  401   c , and a second lateral edge  401   d  opposite the first lateral edge  401   c . The first lateral edge  401   c  and the second lateral edge  401   d  extend from the forward edge  401   a  to the rearward edge  401   b , as shown in  FIG. 6 . The kink  700  of the heat shield panel  400   c  extends from the first lateral edge  401   c  to the second lateral edge  401   d , as shown in  FIG. 6 . The kink  700  of the heat shield panel  400   c  may extend from the first lateral edge  401   c  to the second lateral edge  401   d  about parallel to at least one of the forward edge  401   a  and the rearward edge  401   b.    
     As shown in  FIG. 6 , there may be one or more mounting studs  430  located on the kink  700  of the kinked heat shield  400   c . In the example illustrated in  FIG. 6 , there may be a mounting stud  430  located proximate the kink  700  and proximate the first lateral edge  401   c  and another mounting stud  420  located proximate the kink  700  and proximate the second lateral edge  401   d . Advantageously, locating mounting studs  420  proximate the first lateral edge  401   c  and the second lateral edge  401   d  helps seals the first lateral edge  401   c  and the second lateral edge  401   d  proximate the kink  700  for cooling flow through the impingement cavity  390  (see  FIG. 4 ). Although not shown in  FIG. 6 , there may an additional mounting stud  430  located proximate the kink  700  and about centered between the first lateral edge  401   c  and the second lateral edge  401   d.    
     Referring now to  FIG. 7 , with continued reference to  FIGS. 1-6 , a top view of the shell  600  is illustrated, in accordance with an embodiment of the present disclosure. Various shapes for the mounting orifices  630  located proximate the kink  500  in the shell  600  are illustrated in  FIG. 7 . In one embodiment, a mounting orifice  630  located proximate the kink  500  in the shell  600  may have an oval or slotted shape elongated in a forward-to-aft direction FA 1 , as shown at  630   a , which allows the kinked heat shield panel  400   c  to expand in the forward-to-aft direction FA 1  as a mounting stud  430  slides through the mounting orifice  630 . In another embodiment, a mounting orifice  630  located proximate the kink  500  in the shell  600  may have an oval or slotted shape elongated perpendicular to the forward-to-aft direction FA 1 , as shown at  630   c , which allows the kinked heat shield panel  400   c  to expand perpendicular to the forward-to-aft direction FA 1  as a mounting stud  430  slides through the mounting orifice  630 . In another embodiment, a mounting orifice  630  located proximate the kink  500  in the shell  600  may have an circular shape, as shown at  630   b , which restricts the kinked heat shield panel  400   c  from moving proximate the mounting stud  430  that is located through the mounting orifice  630 . It is understood that that location of the mounting orifices  630  along the kink  500 , their respective shapes, and the combination of different shapes may vary. It is also understood that the mounting orifices  630  located away from the kink  500  are shown as circular for ease of illustration but may have other shapes, including but not limited to oval, slotted, . . . etc, and may have different heights, widths, and dimensions. 
     Technical effects of embodiments of the present disclosure include incorporating a kinked heat shield panel into a combustor to remove gaps previously located between heat shield panels located proximate to kinks in the shell of the combustor. 
     The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, element components, and/or groups thereof. 
     While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.