Abstract:
A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority to U.S. Provisional Application No. 61/908,387, which was filed on Nov. 25, 2013 and is incorporated herein by reference. 
     
    
     STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT 
       [0002]    This invention was made with government support with the United States Navy under Contract No.: N00014-09-D-0821-0006. The government therefore has certain rights in this invention. 
     
    
     BACKGROUND 
       [0003]    This disclosure relates to a gas turbine engine with an adjustable vane. More particularly, the disclosure relates to an adjustable vane sealing arrangement. 
         [0004]    A gas turbine engine uses a compressor section that compresses air. The compressed air is provided to a combustor section where the compressed air and fuel is mixed and burned. The hot combustion gases pass through a turbine section to provide work that may be used for thrust or driving another system component. 
         [0005]    In general, it is often the case that the temperature of the gases passing through the flow path of a turbine stage may exceed a maximum allowable temperature of the turbine vane material, and therefore it is necessary to provide a continuous supply of cooling air to the interior of the airfoil in order to limit its maximum temperature. A turbine section typically has one or more fixed stages and one or more rotatable stages. A typical cooling scheme is to feed the cooling air though openings in fixed stator vanes. Such openings are situated directly over the attached airfoil, such that the cooling air enters directly into passages internal to the airfoil. Inner and outer diameter platforms serve to constrain the stator vane relative to the static structure of the turbine section, and additionally serve to define the inner and outer diameter flow path boundaries. 
         [0006]    In certain designs, variable stator vanes may be used in the fixed stage where the airfoil portion of the vanes is rotatable about a radial axis. In one embodiment, such turbine vanes include an airfoil and a cylindrical trunnion that connects the airfoil to a support structure, such as inner and outer cases, via a set of bushings or bearings. Cooling air may be provided to the airfoil through an aperture in the trunion. There is typically a gap between the moveable airfoil section and the support structure that permits the airfoil section to rotate freely without interference or binding with the support structure. One or more actuators selectively rotates the airfoil section of the variable vanes about the trunions between desired positions. 
       SUMMARY 
       [0007]    In one exemplary embodiment, a gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening. 
         [0008]    In a further embodiment of the above, the platforms include an outer platform having a boss. The boss circumscribes the aperture. 
         [0009]    In a further embodiment of any of the above, the outer platform includes a groove that is opposite the boss and adjacent to the vane. A seal is provided in the groove and is engageable with the vane. 
         [0010]    In a further embodiment of any of the above, a cooling source is in fluid communication with the outer platform. A passageway extends through the boss to the groove and is configured to supply fluid from the cooling source to the seal to urge the seal into engagement with the vane. 
         [0011]    In a further embodiment of any of the above, the aperture is larger than the opening. The seal circumscribes the aperture. 
         [0012]    In a further embodiment of any of the above, the vane is moveable between fully opened and closed positions. The vane opening remains within the seal boundary in the fully opened and closed positions. 
         [0013]    In a further embodiment of any of the above, the opening is an entrance. The cooling passage includes an exit opposite the entrance. The platform includes an inner platform that has a recess that is in fluid communication with the exit. 
         [0014]    In a further embodiment of any of the above, the inner platform includes a groove that is opposite the vane. A seal is provided in the groove and is engageable with the vane. 
         [0015]    In a further embodiment of any of the above, a cooling source is in fluid communication with the outer platform. A passageway extends through the boss to the groove and is configured to supply fluid from the cooling source to the seal to urge the seal into engagement with the vane. 
         [0016]    In a further embodiment of any of the above, the aperture is larger than the opening. The seal circumscribes the aperture. The vane is moveable between fully opened and closed positions. The vane opening remains within the seal boundary in the fully opened and closed positions. 
         [0017]    In a further embodiment of any of the above, the vane is arranged within the turbine section. 
         [0018]    In a further embodiment of any of the above, a circumferential array of fixed and adjustable vanes is included. 
         [0019]    In another exemplary embodiment, an adjustable vane for a gas turbine engine includes an airfoil that is arranged between opposing trunions extending from opposing sealing faces. An opening in one of the sealing faces is laterally spaced from one of the trunions. The airfoil has a cooling passage that is in fluid communication with the opening. 
         [0020]    In a further embodiment of the above, an opening is provided on each of the sealing faces. 
         [0021]    In a further embodiment of any of the above, the trunions are not in fluid communication with the cooling passage. 
         [0022]    In a further embodiment of any of the above, bushings or bearings are supported on each of the trunions. 
         [0023]    In one exemplary embodiment, a method of cooling an adjustable vane for a gas turbine engine includes supporting a vane for rotation relative to a platform about a trunion, and energizing a seal provided between the platforms and the vane to seal a gap between the platforms and the vane. 
         [0024]    In a further embodiment of any of the above, the method includes the step of supplying cooling fluid to the vane from an area adjacent to the trunion. 
         [0025]    In a further embodiment of any of the above, the platform includes an inner platform and an outer platform. The method includes the step of energizing a seal that is provided between at least one of the outer and inner platforms and the vane and engaging the vane with the seal. 
         [0026]    In a further embodiment of any of the above, the supplying step includes providing a cooling fluid to the interior of the vane. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0027]    The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein: 
           [0028]      FIG. 1  is a highly schematic view of an example turbojet engine. 
           [0029]      FIG. 2  is a perspective view of a portion of a variable stage. 
           [0030]      FIGS. 3A and 3B  are top elevational views of the variable stator vane in the fully closed and fully opened positions, respectively. 
           [0031]      FIG. 4  is a perspective view of a portion of a variable stage having fixed vanes with the variable vane removed. 
           [0032]      FIG. 5  is an elevational view of the variable stator vane. 
           [0033]      FIG. 6  is a cross-sectional view through the variable stator vane illustrating a sealing configuration. 
       
    
    
       [0034]    The embodiments, examples and alternatives of the preceding paragraphs, the claims, or the following description and drawings, including any of their various aspects or respective individual features, may be taken independently or in any combination. Features described in connection with one embodiment are applicable to all embodiments, unless such features are incompatible. 
       DETAILED DESCRIPTION 
       [0035]      FIG. 1  illustrates an example turbojet engine  10 . The engine  10  generally includes a fan section  12 , a compressor section  14 , a combustor section  16 , a turbine section  18 , an augmentor section  19  and a nozzle section  20 . The compressor section  14 , combustor section  16  and turbine section  18  are generally referred to as the core engine. An axis A of the engine  10  is generally disposed and extends longitudinally through the sections. An outer engine duct structure  22  and an inner cooling liner structure  24  provide an annular secondary fan bypass flow path  26  around a primary exhaust flow path E. 
         [0036]      FIG. 2  illustrates a portion of a variable stator vane stage  28 , which is provided in the turbine section  14 , for example. It should be understood that the disclosed variable stator vane can be used in the fan or compressor sections, if desired. The disclosed variable stator vane arrangement can be applied to turbojets, low bypass turbofans, high bypass turbofans, geared turbofans, two spool engines, three spool engines, augmented engines, and/or engines with one or more bypass streams. 
         [0037]    A case  30  supports an array of circumferentially arranged fixed and adjustable stator vanes  36 ,  38  extending between radially spaced apart inner and outer platforms  32 ,  34 . The outer platform  34  includes a circumferential channel  40  arranged between forward and aft rails  42 ,  44 . A cooling source  46  is in fluid communication with the channel  40  to supply cooling fluid to the fixed and adjustable vanes  36 ,  38 . 
         [0038]    The adjustable vane  38  includes outer and inner trunnions  48 ,  50  ( FIG. 5 ) each received in a corresponding hole  54  in the inner and outer platforms  32 ,  34 , as best shown in  FIG. 4 . Each trunion  48 ,  50  may have a bushing or a bearing between it and the inner and outer platforms  32 ,  34 . 
         [0039]    Returning to  FIG. 2 , a controller  56  commands an actuator  58  connected to a linkage  60  that is coupled to the outer trunnion  48 . The actuator rotates the airfoil  51  of the adjustable vane  38  between fully closed and fully opened positions, shown in  FIGS. 3A and 3B , respectively, to control the flow of fluid through the engine&#39;s core flow path. 
         [0040]    Cooling fluid is communicated from the cooling source  46  through an aperture  64  extending through a boss  62  in the outer platform  34 , as shown in  FIG. 2 . The adjustable vane  38  includes an opening  66  that provides an entrance to a cooling passage  68  within the airfoil  51 , shown in  FIG. 5 . The airfoil may include multiple film cooling holes  70  in the exterior airfoil surface  72  that are in fluid communication with the cooling passage  68 . The aperture  64  is larger than the opening  66  such that when the adjustable vane  38  is moved between the fully opened and closed positions, the opening  66  remains within the aperture  64 . 
         [0041]    Referring to  FIG. 6 , the outer platform  34  includes a groove  74  opposite the boss  62 . A seal  76  is arranged within the groove  74  and is engageable with a sealing surface  80  of the adjustable vane  38 . The seal  76  circumscribes the aperture  64  and seals an end wall gap  77  provided between the sealing face  80  and the outer platform  34 . Passageways  78  fluidly connect the channel  40  and the groove  74  to supply cooling fluid from the cooling source  46  to the groove  74 , which energizes the seal  76  and urges the seal  76  into engagement with the sealing face  80 . 
         [0042]    Another sealing arrangement is provided at the opposing end of the vane  38 . The inner platform  32  includes a recess  84  that receives the cooling fluid from an exit  82  of the cooling passage  68 . A passageway  178  fluidly connects the recess  84  to a groove  174  in the inner platform  32 . A seal  176  is arranged within the groove  174  and circumscribes the recess  84 . The seal  176  is energized by the cooling fluid to urge the seal  176  into engagement with the sealing face  180  to seal the end wall gap  177 . 
         [0043]    The disclosed sealing arrangement enables cooling fluid to be efficiently communicated to the adjustable vane while minimizing leakage of the cooling air. Transferring the cooling fluid to the adjustable vane at an area adjacent to the trunnion rather than through the trunnion enables an efficient and simple sealing arrangement with a feed area that is not limited by the trunion geometry. 
         [0044]    It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom. 
         [0045]    Although the different examples have specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples. 
         [0046]    Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.