Abstract:
One embodiment is a unique apparatus having a gas turbine engine flange assembly. Another embodiment is a unique system having a gas turbine engine flange assembly. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies. Further embodiments, forms, objects, features, advantages, aspects, embodiments and benefits shall become apparent from the following descriptions, drawings, and claims.

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
       [0001]    The present application claims benefit of U.S. Provisional Patent Application No. 61/428,765, filed Dec. 30, 2010, entitled GAS TURBINE ENGINE FLANGE ASSEMBLY INCLUDING FLOW CIRCUIT, which is incorporated herein by reference. 
     
    
     FIELD OF THE INVENTION 
       [0002]    The present invention relates generally to gas turbine engines and more particularly, but not exclusively, to gas turbine engine flange assemblies having flow circuits therein. 
       BACKGROUND 
       [0003]    Gas turbine engines are an efficient source of useful energy and have proven useful to propel and power aircraft, for electricity generation, as well as for other uses. Gas turbine engines include a number of structures which must be interconnected. Present approaches to interconnection of gas turbine engine structures suffer from a number of disadvantages, limitations, and drawbacks, for example, those respecting weight, mass, complexity, thermal stress, thermal mismatch, ease of assembly or disassembly, part count, engine envelope, engine profile, and others. Thus, there is a need for unique and inventive apparatuses, systems, and methods of interconnecting gas turbine engine structures. 
       SUMMARY 
       [0004]    One embodiment is a unique apparatus having a gas turbine engine flange assembly. Another embodiment is a unique system having a gas turbine engine flange assembly. Still other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies. Further embodiments, forms, objects, features, advantages, aspects, embodiments and benefits shall become apparent from the following descriptions, drawings, and claims. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0005]      FIG. 1  is a generalized schematic representation illustrating some aspects of a non-limiting example of a gas turbine engine in accordance with an embodiment of the present invention. 
           [0006]      FIG. 2  is a perspective view of an aircraft including gas turbine engines configured for aircraft propulsion. 
           [0007]      FIG. 3  is a side sectional view illustrating some aspects of a non-limiting example of a flange assembly in accordance with an embodiment of the present invention. 
           [0008]      FIG. 4  is a perspective sectional view illustrating some aspects of the flange assembly of  FIG. 3 . 
           [0009]      FIG. 5  is a perspective sectional view illustrating some aspects of the flange assembly of  FIG. 3 . 
       
    
    
     DETAILED DESCRIPTION 
       [0010]    For purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated device, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates. 
         [0011]    With reference to  FIG. 1 , there is illustrated some aspects of a non-limiting example of a generalized representation of a gas turbine engine  11  in accordance with an embodiment of the present invention. Gas turbine engine  11  includes a compressor section  12 , a combustor section  13 , and a turbine section  14 , which are integrated together. It is important to realize that there are multitudes of ways in which gas turbine engine components can be linked together. In one form, gas turbine engine components are integrated to produce an aircraft flight propulsion engine generally referred to as a turbo-fan. Another form of a gas turbine engine includes a compressor section, a combustor section, and a turbine section integrated to produce an aircraft flight propulsion engine without a fan section. It should be understood that the present invention is applicable to all types of gas turbine engines, and is not limited to the embodiments illustrated and described herein. Embodiments of the present invention may be employed, for example and without limitation, in gas turbine engines that are configured for use in other applications, such as pumping sets for gas and oil transmission lines, electricity generation, naval propulsion and/or power generation, vehicle propulsion and auxiliary power units. It is also important to realize that there are a multitude of additional components which can be used in gas turbine engines. For example, additional compressor and turbine stages could be present with intercoolers connected between the compressor stages. 
         [0012]    With reference to  FIG. 2  there is illustrated an aircraft  200  including gas turbine engines  210  which are configured for aircraft propulsion. It should be understood that the term “aircraft” includes helicopters, airplanes, missiles, unmanned space devices, transatmospheric vehicles and other substantially similar devices. 
         [0013]    With reference to  FIG. 3 , there is illustrated a side sectional view illustrating some aspects of a non-limiting example of a gas turbine engine flange assembly  300  in accordance with an embodiment of the present invention. Flange assembly  300  includes a flange  310 , a flange  320 , and a flange  330 . Flange  320  is positioned intermediate (between) the flange  310  and the flange  330 . Flange  310  extends from case  311 , flange  320  extends from support  321 , and flange  330  extends from case  331 . A shim plate  312 A is positioned intermediate flange  310  and flange  320 . A shim plate  312 B is positioned intermediate flange  320  and flange  330 . Further embodiments may include additional shim plates or may omit one or both of shim plates  312 A and  312 B. 
         [0014]    In the embodiment illustrated in  FIG. 3 , case  311  is an outer combustor case, support  321  is a diffuser support, and case  331  is a compressor case. in other embodiments, case  311 , support  321  and case  331  may represent other engine  11  components, e.g., cases and/or supports. For example in another exemplary embodiment, flange  330  extends from case  331  in the form of an outer combustor case, flange  320  extends from support  321  in the form of a turbine support, flange  310  extends from case  311  in the form of a turbine case, and flange  320  is positioned intermediate flange  330  and flange  310 . In a further exemplary embodiment, flange  330  extends from case  331  in the form of a turbine case, flange  320  extends from support  321  in the form of a turbine support or an afterburner support, flange  310  extends from case  311  in the form of an afterburner case, and flange  320  is positioned intermediate flange  330  and flange  310 . In further exemplary embodiments, a flange positioned intermediate inner and outer flanges may be independent of a case or support and may be present primarily or exclusively to help define a flow circuit in a flange assembly. Further embodiments include flanges which are fastened to or coupled to cases, supports and/or other structure(s). Additional embodiments contemplate assemblies including a flange positioned adjacent at least one other flange where the flanges extend from or are coupled to other gas turbine cases, supports, or other structures. 
         [0015]    With continuing reference to  FIG. 3 , a higher pressure cavity  340  is bordered by case  311  and support  321 , and a lower pressure cavity  350 , having a low pressure than high pressure cavity  340 , is bordered by support  321  and case  331 . It should be understood that additional structure(s) may also border higher pressure cavity  340  and lower pressure cavity  350 . In the embodiment illustrated in  FIG. 3 , higher pressure cavity  340  is a bleed air cavity which contains pressurized working fluid received from a gas turbine engine compressor, and lower pressure cavity  350  contains fluid at a lower pressure than higher pressure cavity  340 . Other embodiments contemplate other higher pressure cavities, for example, bypass cavities, or other cavities which receive working fluid from a compressor or from other gas turbine engine sections or stages, and other lower pressure cavities which contain fluid at a lower pressure than their respective higher pressure cavities. 
         [0016]    A flow circuit interconnects higher pressure cavity  340  and lower pressure cavity  350  and provides a route for fluid to flow through flange assembly  300 . A pressure differential between higher pressure cavity  340  and lower pressure cavity  350  causes fluid to flow through the flow circuit. From higher pressure cavity  340 , fluid flow enters recess  316  and proceeds to fillet cavity  317 . From fillet cavity  317  fluid flow proceeds to passage  319 . From passage  319  fluid flow proceeds to hole  318  which is provided in flange  320 . From hole  318  fluid flow proceeds to passage  329 . From passage  329 , fluid flow proceeds to fillet cavity  327 . From fillet cavity  327 , fluid flow proceeds to recess  326 . From recess  326 , fluid flow proceeds to lower pressure cavity  350 . Recess  316  is defined in flange  320  and faces flange  310 . In other embodiments, recess  316  can be defined in flange  310  facing flange  320 . Recess  326  is defined in flange  320  and faces flange  330 . In other embodiments, recess  326  can be defined in flange  330  facing flange  320 . In the illustrated embodiment, passages  319  and  329  are provided by shim plates  312 A and  312 B, respectively. In other embodiments, passages  319  and/or  329  can be provided in flanges  310 ,  320 , and/or  330 , for example, using machining techniques. 
         [0017]    With reference to  FIG. 4 , there is illustrated a perspective sectional view of some aspects of a non-limiting example of flange assembly  300  in accordance with an embodiment of the present invention. While only a portion of flange assembly  300  is illustrated in  FIG. 4 , it is contemplated that flange assembly  300  could extend about all or a portion of the circumference of cases  311  and  331 . Features described above in connection with  FIG. 3  are indicated with identical reference numerals in  FIG. 4 . Fasteners  370  may pass through flanges  310 ,  320  and  330  and shim plates  312 A and  312 B to fasten the flange assembly  300  together. Additional embodiments contemplate other means for fastening flange assembly  300  including welding, other fasteners, and/or combinations of these and other techniques. 
         [0018]    As illustrated by arrows F, fluid flow from higher pressure cavity  340  enters recess  316  and proceeds to fillet cavity  317  which extends along the entire circumference of flange assembly  300 . In other embodiments, fillet cavity  317  can extend along only a portion of the circumference of flange assembly  300 . In other embodiments, a number of fillet cavities can extend along portions of the circumference of flange assembly  300 . Flow can proceed in either direction along fillet cavity  317  and into passage  319  opposite recess  316 . The number of recesses  316  provided in flange assembly  300  may vary, e.g., depending upon the desired amount of flow through flange assembly  300 . As illustrated in  FIG. 4 , there are a number of passages  319  provided in flange assembly  300 . Furthermore, there may also be additional recesses similar to recess  316  provided in flange assembly  300 . From passages  319 , flow proceeds through holes  318  provided in flange  320 . In the embodiment illustrated in  FIG. 4 , two holes  318  are positioned near the distal corners of the passage  319 . This position provides a preferred fluid flow through passage  319 . Other embodiments contemplate different numbers and positioning of holes, for example, one, three, four or more holes could be provided in a variety of positions. Further embodiments contemplate that the holes could be a variety of different shapes, for example, ellipsoid shapes, slots, and other openings could be provided in flange  320 . Additional embodiments contemplate that a variety of different sizes of holes or other openings could be provided in flange  320 , for example, larger openings, smaller openings, and combinations of different sizes of openings. Further embodiments contemplate that flow across flange  320  could proceed around an end of flange  320  rather than through one or more openings provided through flange  320 . In such embodiments flange  320  may extend radially along only part of flanges  310  and  330  and one or more flow paths could be positioned at an end of flange  320 . An additional structure could be positioned intermediate flanges  310  and  330  to define one or more flow paths positioned at the end of flange  320 . Alternatively, a portion of flange  310 , flange  330 , or both could extend to define the flow path(s) positioned at the end of flange  320 . 
         [0019]    With reference to  FIG. 5 , there is illustrated a perspective view of some aspects of a non-limiting example of a portion of flange assembly  300  in accordance with an embodiment of the present invention. While only a portion of flange assembly  300  is illustrated in  FIG. 5 , it is contemplated that flange assembly  300  could extend about all or a portion of the circumference of cases  311  and  331 . Features described above in connection with  FIGS. 3 and 4  are indicated with identical reference numerals in  FIG. 5 . Arrows F illustrate the flow of fluid through flange assembly  300 . As indicated by arrows F, fluid flows from holes  318  into passages  329 . From passages  329 , fluid flow enters fillet cavity  327  which extends along the circumference of flange assembly  300 . In other embodiments, fillet cavity  327  can extend along a portion of the circumference of flange assembly  300 . In other embodiments, a number of fillet cavities can extends along portions of the circumference of flange assembly  300 . From fillet cavity  327 , fluid flow can proceed in either direction along fillet cavity  327 , or can enter recess  326 . From recess  326 , flow enters lower pressure cavity  350 . The number of recesses  326  provided in flange assembly  300  may vary, e.g., depending upon the desired amount of flow through flange assembly  300 . Recesses  316  and  326  and passages  319  and  329  are preferably intermittently spaced so that they do not interfere with the piloting provided by flanges  310 ,  320  and  330 . 
         [0020]    In a preferred embodiment, the flow circuit of flange assembly  300  can provide desirable thermal response. During engine operation outer combustor case  311  is subjected to high temperatures resulting from the combustion process in the combustor section of a gas turbine engine. The flange assembly  300  is subjected to the relatively lower temperature of its environment. A temperature mismatch between the case  311  and the flange assembly  300  can result and may produce undesirable thermally induced stress. Flow through the flow circuit provided in flange assembly  300  can increase the thermal response of the flange assembly and decrease the temperature mismatch and thermally induce stress that might otherwise be present. 
         [0021]    Embodiments of the present invention include an apparatus comprising: a gas turbine engine flange assembly including: a first flange, a second flange, and a third flange, the second flange being positioned intermediate the first flange and the third flange; and a fluid flow circuit extending intermediate the first flange and the second flange, across the second flange, and intermediate the second flange and the third flange. 
         [0022]    In a refinement, the apparatus further comprises a shim plate positioned intermediate the first flange and the second flange. 
         [0023]    In another refinement, the apparatus further comprises a shim plate positioned intermediate the second flange and the third flange, the shim plate defining a boundary of a portion of the fluid flow circuit. 
         [0024]    In yet another refinement, the apparatus further comprises a fillet cavity intermediate the first flange and the second flange. 
         [0025]    In still another refinement, the apparatus further comprises a fillet cavity intermediate the second flange and the third flange, the fillet cavity defining a boundary of a portion of the fluid flow circuit. 
         [0026]    In yet still another refinement, the apparatus further comprises a recess provided in one of the first flange, the second flange, and the third flange, the recess defining a boundary of a portion of the fluid flow circuit. 
         [0027]    In an additional refinement, the apparatus further comprises means for routing fluid flow through the flange assembly. 
         [0028]    In a further refinement, the flow circuit extends from a higher pressure cavity to a lower pressure cavity and includes a first recess provided in the second flange, a first fillet cavity intermediate the first flange and the second flange, a first passage bordered by first a shim plate, the first flange and the second flange, at least one opening provided in the second flange, a second passage bordered by a second shim plate, the second flange and the third flange, a second fillet cavity intermediate the second flange and the third flange, and a second recess provided in the second flange. 
         [0029]    In a yet further refinement, the first flange extends from a compressor case, and the third flange extends from an outer combustor case. 
         [0030]    In a still further refinement, the first flange extends from an outer combustor case, and the third flange extends from a turbine case. 
         [0031]    In a yet still further refinement, the first flange extends from a combustor case, and the third flange extends from an afterburner case. 
         [0032]    In another further refinement, the second flange extends from a support. 
         [0033]    Embodiments of the present invention include a system comprising: a first gas turbine engine case; a second gas turbine engine case; a flange assembly coupling the first gas turbine engine case and the second gas turbine engine case, the flange assembly extending circumferentially about at least a portion of the first gas turbine engine case; and a fluid flow circuit extending from a cavity within the first gas turbine engine case to an interior portion of the flange assembly. 
         [0034]    In a refinement, the flange assembly includes a first flange, a second flange, and a third flange, the second flange being positioned intermediate the first flange and the third flange. 
         [0035]    In another refinement, the fluid flow circuit extends from a higher pressure cavity to a lower pressure cavity and includes a first flow passage intermediate the first flange and the second flange, an opening provided in the second flange, and a second flow passage intermediate the second flange and the third flange. 
         [0036]    In yet another refinement, the first gas turbine engine case is a combustor case and the second gas turbine engine case is a compressor case. 
         [0037]    In still another refinement, the first gas turbine engine case is a combustor case and the second gas turbine engine case is a turbine case. 
         [0038]    In yet still another refinement, the first gas turbine engine case is an afterburner case and the second gas turbine engine case is a turbine case. 
         [0039]    Embodiments of the present invention include a method comprising: operating a gas turbine engine including a compressor, a combustor, a turbine, a flange assembly including a first flange extending from an engine case, a second flange, and a third flange; generating a temperature differential between a portion of the engine case and the flange assembly based upon the operating; and flowing fluid through a flow circuit in the flange assembly effective to reduce the temperature differential. 
         [0040]    In a refinement, the flowing fluid through a flow circuit in the flange includes flowing fluid through a passage intermediate the first flange and the second flange. 
         [0041]    In another refinement, the flowing fluid through a flow circuit in the flange includes flowing fluid through a hole provided in the second flange. 
         [0042]    In yet another refinement, the engine case is an outer combustor case. 
         [0043]    While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment(s), but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims, which scope is to be accorded the broadest interpretation so as to encompass all such modifications and equivalent structures as permitted under the law. Furthermore it should be understood that while the use of the word preferable, preferably, or preferred in the description above indicates that feature so described may be more desirable, it nonetheless may not be necessary and any embodiment lacking the same may be contemplated as within the scope of the invention, that scope being defined by the claims that follow. In reading the claims it is intended that when words such as “a,” “an,” “at least one” and “at least a portion” are used, there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. Further, when the language “at least a portion” and/or “a portion” is used the item may include a portion and/or the entire item unless specifically stated to the contrary.