Patent Abstract:
A gas turbine engine has an intermediate case. At least one compressor exit stator shroud is welded to the intermediate case.

Full Description:
BACKGROUND OF THE INVENTION  
       [0001]     (1) Field of the Invention  
         [0002]     The invention relates to gas turbine engines. More particularly, the invention relates to the mounting of low pressure compressor exit stators to turbine engine intermediate cases.  
         [0003]     (2) Description of the Related Art  
         [0004]      FIG. 1  shows a gas turbine engine  20  having a case assembly  22  containing concentric high and low pressure rotor shafts  24  and  25 . The shafts are mounted within the case for rotation about an axis  500  which is normally coincident with central longitudinal axes of the case and shafts. The high pressure rotor shaft  24  is driven by the blades of a high pressure turbine section  26  to in turn drive the blades of a high pressure compressor  27 . The low pressure rotor shaft  25  is driven by the blades of a low pressure turbine section  28  to in turn drive the blades of a low pressure compressor section  29  and a fan  30 . Air passes through the engine along a core flowpath  502  sequentially compressed by the low and high compressor sections  29  and  27 , then passing through a combustor  32  wherein a portion of the air is combusted along with a fuel, and then passing through the high and low turbine sections  26  and  28  where work is extracted. Additional air is driven by the fan along a bypass flowpath  504 .  
         [0005]      FIG. 2  shows the core flowpath  502  at the downstream end of the low pressure compressor section. A final ring of compressor blades  50  is mounted to an aft compressor disk  52  of the low speed spool. Upstream of the blades  50  is a ring of vanes  54  secured at their outboard ends to a compressor case assembly  56  and at their inboard ends having a seal system for sealing with the low speed spool. Downstream of the vanes  50  is an exit stator  60  having an array of vanes  62  extending between inner (inboard) and outer (outboard) stator shrouds  64  and  66 . The stator shrouds have respective outboard and inboard surfaces  67  and  68  which locally form inboard and outboard boundaries of the core flowpath. At downstream ends, the shrouds  64  and  66  have mounting flanges  70  and  71  bolted to associated flanges  72  and  73  respectively extending inward and outward from respective forward portions of respective inboard and outboard walls  74  and  75  of an intermediate case  76 . The inboard and outboard walls  74  and  75  (although not necessarily inboardmost and outboardmost) are connected by an array of webs or struts  77 . In the exemplary embodiment, a bearing support  80  is also bolted to the flange  72  outboard of a bearing compartment.  
         [0006]     The intermediate case  76  is an important structural element of the engine providing a load path for the engine thrust and providing transverse stiffness. Exemplary intermediate cases are formed essentially as castings with subsequent machining and addition of minor components such as threaded inserts for receiving the bolts. The shrouds  64  and  66  are subject to different loads. Although the shrouds may be of like composition (e.g., titanium alloy) to the intermediate case, they may advantageously be made in different ways (e.g., stamping of sheet stock or forging) to provide the desired strength parameters. In an exemplary method of engine assembly, the stator vanes may be preassembled to the shrouds and the stator then bolted to the intermediate case as a unit. The preassembly may involve inserting the vanes through apertures in the shrouds, with a stablug portion  84  at the tip of the vane airfoil protruding beyond the outboard surface of the outboard shroud and being sealed thereto by an encapsulant such as RTV Silicone™. At the inboard end of the airfoil, a transversely extending foot  86  may have an outboard surface facing the inboard surface of the inboard shroud (e.g., contacting). The foot may be secured to the shroud via fasteners such as rivets (not shown).  
       SUMMARY OF THE INVENTION  
       [0007]     Accordingly, one aspect of the invention involves a gas turbine engine. A compressor section has a number of rings of blades and vanes. A turbine section is downstream of the compressor section along a core flowpath of the engine. An intermediate case has inboard and outboard portions forming inboard and outboard walls for the core flowpath. At least a first of the rings of the compressor section vanes extends between inboard and outboard stator shrouds. At least a first of the stator shrouds is welded to the intermediate case.  
         [0008]     In various implementations, the compressor section may be a low pressure compressor section and the engine may further include a high pressure compressor section downstream thereof. The first ring may be a downstreammost one of the rings. The inboard and outboard stator shrouds may be respectively welded to the intermediate case inboard and outboard portions. Each of the inboard and outboard stator shrouds may be a full annulus. The first of the inboard and outboard stator shrouds may be a forging or a stamping. The intermediate case may be a casting. Each of the compressor vanes may have an inboard foot with an airfoil extending outboard from the foot. Each foot may be secured to the inboard shroud via fasteners, with an outboard surface of the foot facing an inboard surface of the inboard shroud. Each vane may extend through an associated aperture in the outboard shroud. Each vane may have a stablug and an outboard end of the airfoil protruding beyond an outboard surface of the outboard shroud and sealed relative to the outboard shroud.  
         [0009]     Another aspect of the invention involves a method for remanufacturing such a gas turbine engine. A first of the inboard and outboard stator shrouds is removed. A replacement shroud is welded in place of the first shroud. In various implementations, replacement vanes may individually be installed to the replacement shroud in place of the first ring of the compressor vanes after the welding.  
         [0010]     Another aspect of the invention involves a method for reengineering a gas turbine engine configuration from a first configuration to a reengineered configuration. The first configuration has compressor exit stator inboard and outboard shrouds secured to first and second portions of an intermediate case by first and second groups of fasteners. The first and second groups of fasteners are engaged to first and second groups of fastener-receiving features of the intermediate case. The initial configuration is altered to reengineered configuration having a reengineered intermediate case welded to a reengineered at least one of the exit stator inboard and outboard shrouds.  
         [0011]     Another aspect of the invention involves a method for retrofitting a gas turbine engine. Compressor exit stator inboard and outboard shrouds are initially secured to first and second portions of intermediate case by first and second groups of fasteners engaged to first and second groups of fastener-receiving features of the intermediate case. According to the method, the shrouds are removed. A portion of the intermediate case at least partially containing at least one of the first and second groups of fastener-receiving features is then destructively removed. A replacement stator shroud may then be welded to the intermediate case.  
         [0012]     The details of one or more embodiments of the invention are set forth in the accompanying drawings and the description below. Other features, objects, and advantages of the invention will be apparent from the description and drawings, and from the claims. 
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0013]      FIG. 1  is a partially schematic longitudinal sectional view of an exemplary prior art gas turbine engine.  
         [0014]      FIG. 2  is a view of a compressor exit of the engine of  FIG. 1 .  
         [0015]      FIG. 3  is a view of a compressor exit according to principles of the invention.  
     
    
       [0016]     Like reference numbers and designations in the various drawings indicate like elements.  
       DETAILED DESCRIPTION  
       [0017]      FIG. 3  shows a similar portion of the flowpath  502  through an engine which may be a remanufacturing of the engine of  FIG. 2  or may be of a configuration representing a reengineering of the configuration of the engine  FIG.2 . Like components are shown with like numbers to their counterparts of  FIG. 2 . An alternate intermediate case  120  has inboard and outboard walls  122  and  124  and struts  126  generally similar to analogous elements of  FIG. 2 . Similarly, a flange  128  extends inboard from the inboard wall  122  for connection with the bearing support. The case  120  lacks the  FIG. 2  features for mounting stator shrouds. Inboard and outboard stator shrouds  130  and  132  similarly lack the  FIG. 2  mounting features. In the exemplary embodiment, the inboard shroud  130  has respective outboard and inboard surfaces  133  and  134  and the outboard shroud has respective inboard and outboard surfaces  135  and  136 . Aft rim portions  140  and  142  of the inboard and outboard shrouds are respectively welded to forward rim portions  144  and  146  of the intermediate case inboard and outboard walls  122  and  124 . The welding saves the weight of the mounting bolts and the associated mating features of the intermediate case. Additionally, the welding potentially reduces costs through simplification of the shrouds and intermediate case and through elimination of various mounting hardware. Additionally, the use of welding may limit the chances of leakage between the shrouds and intermediate case.  
         [0018]     An exemplary assembly method may involve first welding the shrouds to the intermediate case. The vanes may then be installed as in the prior art or otherwise. In repair situations, the vanes may be individually removed and replaced. If necessary to repair or replace one or both of the shrouds, such shroud(s) may be cut off or unwelded and replacement shroud(s) welded in place. To permit such rewelding, advantageously, the forward rim portions of the intermediate case walls may be slightly thickened relative to other portions.  
         [0019]     One or more embodiments of the present invention have been described. Nevertheless, it will be understood that various modifications may be made without departing from the spirit and scope of the invention. For example, the invention may be applied to a variety of existing turbine engine configurations or to configurations yet developed. When applied as a reengineering, the engineering may include additional changes while leaving other aspects of the engine unchanged. In some situations it may be desired that only one of the shrouds be welded in place. Accordingly, other embodiments are within the scope of the following claims.

Technology Classification (CPC): 5