Abstract:
A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the depression to engage the outer tubular member and facilitate sealing thereof.

Description:
TECHNICAL FIELD 
       [0001]    The application relates generally to gas turbine engines and, more particularly, to the bleed air system of a gas turbine engine and to fluid transfer tubes used therein. 
       BACKGROUND 
       [0002]    Gas turbine engine bleed air systems are typically used to bleed air from a compressor section of the engine, and to further transfer this bleed air to other parts of the engine or aircraft for further usage. It is desirable to minimize leakage in bleed air conveying components. However, when subjected to vibratory loads, angular deflections, radial deflections, high temperatures and/or differential thermal growth, the fluid transfer tube assemblies in a bleed system may become worn, unsealed and/or may begin to leak. Elastomeric seals are generally not for use in a high temperature environment, because they may lose their shape and become deformed during use, which may lead to the transfer tube assembly becoming unsealed. Typical seals in gas turbine engine bleed systems are therefore generally metallic and energized through the pressurized air which maintains the seal in place. However, when subjected to angular deflections, known arrangements might lead to leaking. Hence, opportunities exist for improvement. 
       SUMMARY 
       [0003]    In one aspect, there is provided a bleed air system for directing bleed air from a compressor section of a gas turbine engine, the bleed air system comprising a cylindrical adaptor in fluid communication with the compressor section, the adaptor having an inner surface, a cylindrical conduit defined by an outer cylindrical wall having two opposed open ends for permitting fluid passage therethrough, the outer cylindrical wall having a pair of adjacent annular flanges extending radially outwardly in proximity of a respective one of the open ends, the pair of annular flanges defining a circumferential groove between opposed annular side walls thereof and being circumscribed by the cylindrical adaptor, and a non-elastomeric ring received in the circumferential groove, the ring having two opposed annular walls located adjacent a respective one of the two side walls of the flanges, the ring having a radial thickness greater than a depth of the groove such that an outer peripheral portion of the ring protrudes radially from the groove around an entire circumference thereof, the outer peripheral portion having an outer peripheral surface abutting the inner surface of the adaptor and maintaining the adaptor spaced apart from the conduit in proximity of the ring while sealing the conduit within the adaptor, the outer peripheral surface having a curved profile extending between the opposed annular walls along a longitudinal direction configured to provide continuous abutment of the outer peripheral surface on the inner surface irrespective of angular displacement of the cylindrical adaptor relative to the cylindrical conduit, the ring being spaced apart from an inner circumferential surface defining a bottom of the groove along at least a portion of the circumference of the groove such as to create a radial gap permitting relative movement between the ring and the cylindrical conduit. 
         [0004]    In another aspect, there is provided a fluid-conveying device comprising an inner tubular member having two opposed open ends, at least one circumferential portion of the inner tubular member adjacent one of the open ends having an outer annular surface and an annular depression defined therein by two opposed annular side walls extending radially inwardly from the outer surface and interconnected by a circumferential surface spaced radially inwardly from the outer annular surface, a non-elastomeric ring occupying an annular portion of the depression, the ring having an inner diameter greater than a first outer diameter defined by the circumferential surface and smaller than a second outer diameter defined by the outer annular surface near the depression such as to enable radial displacement of the ring within the annular depression while maintaining an inner annular portion of the ring inside the depression, the ring having opposed annular ring walls located adjacent a respective one of the side walls defining the depression and an outer peripheral surface with a rounded contour extending between the annular ring walls along a longitudinal direction, the ring defining an outer diameter greater than the second outer diameter, and an outer tubular member having an inner surface abutting the outer peripheral surface of the ring, the outer tubular member having an inner diameter at least substantially equal to the outer diameter of the ring and being sealingly engaged thereto, the ring maintaining the outer tubular member distanced from the inner tubular member. 
         [0005]    In a further aspect, there is provided a bleed air transfer tube assembly for a gas turbine engine, the tube assembly comprising an inner tubular member having opposed open ends and at least one annular groove defined in an outer surface thereof in proximity of a respective one of the open ends, an outer tubular member surrounding at least a portion of the inner tubular member where the groove is defined, the outer and inner tubular members being relatively sized such as to allow a range of relative angular displacement therebetween, and a non-elastomeric ring received within the annular groove and having opposed radial surfaces extending adjacent radial walls of the annular groove, an outer surface defining a curve along a longitudinal direction between the opposed radial surfaces and in sealed contact with an inner wall of the outer tubular member, and an inner surface extending within the groove, the inner surface of the ring being spaced apart from a bottom of the groove around at least part of its circumference throughout the range of relative angular displacement, the ring having a radial thickness larger than a radial depth of the groove, such that the outer surface of the ring is in continuous contact with the inner wall of the outer tubular member and prevents contact between the inner and outer tubular members in proximity of the groove throughout the range of relative angular displacement. 
     
    
     
       DESCRIPTION OF THE DRAWINGS 
         [0006]    Reference is now made to the accompanying figures in which: 
           [0007]      FIG. 1  is a schematic side cross-sectional view of a gas turbine engine; 
           [0008]      FIG. 2  is a schematic front cross-sectional view of the gas turbine engine of  FIG. 1 ; 
           [0009]      FIG. 3  is a perspective view of an inner tubular member of a transfer tube assembly which can be used in a gas turbine engine such as shown in  FIG. 1 ; 
           [0010]      FIG. 4  is a cross-sectional view of one end of the transfer tube assembly of  FIG. 3 ; 
           [0011]      FIG. 5  is an enlarged view of detail A of  FIG. 4 ; 
           [0012]      FIG. 6  is an enlarged view of detail B of  FIG. 4 ; 
           [0013]      FIG. 7  is a cross-sectional view of part of a transfer tube assembly according to an alternate embodiment; and 
           [0014]      FIG. 8  is a cross-sectional view of part of a transfer ube assembly according to another alternate embodiment. 
       
    
    
     DETAILED DESCRIPTION 
       [0015]      FIG. 1  illustrates a gas turbine engine  10  of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan  12  through which ambient air is propelled, a compressor section  14  for pressurizing the air, a combustor  16  in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section  18  for extracting energy from the combustion gases. The fan  12 , compressor section  14 , combustor  16  and turbine section  18  are surrounded by an outer bypass duct structure  6  which defines a bypass air cavity  4  therearound. 
         [0016]    Referring to  FIGS. 1 and 2 , the gas turbine engine also comprises a bleed air system which bleeds air from the compressor section  14 , and which includes two transfer tube assemblies  8 . The transfer tube assembly  8  is used to direct bleed air from one location to another. The transfer tube assemblies  8  extend through the bypass air cavity  4 , between the compressor section  14  and the outer bypass duct structure  6 . In other embodiments, the transfer tube assembly can be used in various other stages of bleed, for example in bleeding air from the compressor section  14  to the bypass air cavity  4 , as shown by  8 ′ ( FIG. 1 ). 
         [0017]    Referring to  FIG. 4 , the transfer tube assembly  8 ,  8 ′ comprises three main components, a cylindrical conduit or inner tubular member  20 , a cylindrical adaptor or outer tubular member  50  and a single non-elastomeric ring  40  sealing the inner tubular member  20  to the outer tubular member  50 . The inner tubular member  20  and the outer tubular member  50  undergo a range of relative axial and angular deflections, due to thermal growth variations and to vibration loads. The ring  40  provides a sealed contact between the tubular members  20  and  50 , while accommodating such relative motions therebetween. 
         [0018]    As seen in  FIG. 3 . the inner tubular member  20  comprises a cylindrical wall  22  defining two opposed open ends  70 ,  72  for permitting fluid passage therethrough. In the particular embodiment shown, both ends  70 ,  72  of the inner tubular member  20  are relatively similar, with the ring  40  sealing one end  70  of the inner tubular member  20  to the outer tubular member  50  and a second ring  41 , similar to ring  40 , sealing the end  72  of the inner tubular member  20  to a second outer tubular member (not shown), similar to outer tubular member  50 . Only the assembly of the first ring  40 , outer tubular member  50  and inner tubular member  20  at end  70  will be herein described and it is understood that the second end  72  of the inner tubular member  20 , second outer tubular member (not shown) and second ring  41  are similarly configured. In another embodiment, the second end  72  of the inner tubular member  20  may be connected to another component of the gas turbine engine through another type of connection, e.g. a rigid connection. 
         [0019]    As seen in  FIG. 4 , the inner tubular member  20  comprises at least one circumferential portion  26  located in proximity of the end  70  and extending radially outwards from a remainder of the inner tubular member  20 , i.e. the circumferential portion  26  defines has a larger outer diameter than that of a remainder of the inner tubular member  20 . This circumferential portion  26  has an outer annular surface  28  having an annular depression or circumferential groove or depression  30  defined therein. In the embodiment shown, the circumferential portion  26  comprises two adjacent annular flanges  32  interconnected by a circumferential surface  36  and extending radially outwardly therefrom, such that the groove  30  is defined between respective opposed annular side walls  34  of the flanges  32 , with a bottom of the groove  30  being defined by the circumferential surface  36 . In another embodiment which is not shown, the circumferential portion  26  may have an outer diameter similar or substantially similar to that of the outer diameter of the remainder of the inner tubular member  20 , i.e. the thickness and/or configuration of the cylindrical wall  22  may be such that the circumferential portion  26  does not significantly extend radially from a remainder of the inner tubular member  20 . 
         [0020]    Still referring to  FIG. 4 , the ring  40  occupies an annular portion of the groove  30 . The ring  40  has an inner diameter  54  which is greater than a first outer diameter  56  of the inner tubular member  20  defined along the bottom of the groove  30 , by the circumferential surface  36 . As such, the ring  40  is spaced apart from the circumferential surface  36  of the groove  30  along at least a portion of the circumference thereof, therefore creating a variable radial gap  38  between the ring  40  and the circumferential surface  36  (also shown in  FIG. 6 ). The gap  38  allows for relative displacement of the ring  40  inside the groove  30 . The inner diameter  54  of the ring is also smaller than a second outer diameter  58  of the inner tubular member  20  defined by the outer annular surface  28  of the circumferential portion  26  This prevents the ring  40  from exiting the groove  30  during use. 
         [0021]    As seen in  FIG. 5 , the ring  40  has a longitudinal width W, i.e. the dimension measured along longitudinal axis  44  (see  FIG. 4 ), which is slightly smaller than the distance between the side walls  34 , so that the two opposed radial annular side walls  42  of the ring  40  are located adjacent a respective one of the annular side walls  34  and may each abut a respective one of the annular side walls  34 . The ring  40  is in sealing contact with at least one of the side walls  34 , while being free to move relatively thereto, such as to allow movement of the ring  40  within the groove  30  while preventing fluid leakage between the ring  40  and the inner tubular member  20 . 
         [0022]    The ring  40  has a radial thickness T which is greater than a depth D of the groove  30 , to ensure that the ring  40  has an outer peripheral portion  46  protruding from the groove  30  along an entire circumference thereof, regardless of the position of the ring  40  inside the groove  30 . 
         [0023]    In the embodiment shown, the ring  40  is a monolithic, one-piece ring (See  FIG. 3 ) and is split, i.e. it has a circumferential gap  86  extending along part of a circumference thereof. This gap  86  allows for radial compression of the ring  40  and for easy assembly of the ring  40  inside the groove  30 . The ring  40  is made of a stiff material which is resistant to deformation. The ring  40  therefore mechanically seals the inner tubular member  20  and the outer tubular member  50 , such that even under high pressure, the stiffness of the ring allows the ring to maintain its shape. This prevents the ring  40  from collapsing into the groove  30 , thereby preventing the inner tubular member  20  from contacting the outer tubular member  50 . The ring is made of a material which minimizes the risk of the transfer tube assembly  8 ,  8 ′ becoming unsealed when exposed to high temperatures, and which is able to accommodate for thermal growth between the tubular members. In a particular embodiment, the material from which the ring is formed is able to resist to temperatures of at least 1000° F. In one embodiment, the non-elastomeric ring  40  is made of a suitable high temperature metal such as a nickel alloy, for example AMS 5671. In another embodiment, the ring  40  is made of a suitable type of ceramic. In a particular embodiment, the ring  40 , which may be made of a nickel alloy or of another suitable material, is coated on its outer peripheral surface  48  with a thin layer (e.g. 0.0007-0.0013 inches) of an anti-galling compound, for additional wear protection. 
         [0024]    Referring back to  FIG. 4 , the outer tubular member  50  surrounds or circumscribes the ring  40  and at least a portion of the inner tubular member  20  where the groove  30  is defined. The outer tubular member  50  has an inner surface  52  defining an inner diameter  62  substantially equal to the outer diameter  60  of the outer peripheral surface  48  of the ring  40 . The inner surface  52  therefore abuts the outer peripheral surface  48  to form a sealed connection. This prevents fluid leakage between the outer tubular member  50  and the ring  40 . 
         [0025]    As mentioned above, the ring  40  has an outer peripheral portion  46  which protrudes radially from the groove  30  along an entire circumference thereof. The ring  40  is therefore the only connection between the inner tubular member  20  and the outer tubular member  50 , and it maintains the inner tubular member  20  and the outer tubular member  50  spaced apart. Therefore, the risk of inner tubular member  20  directly contacting the outer tubular member  50  is minimized, which ensures that contact is limited to the surfaces designed to withstand wear, thus reducing wear damage of the tubular members  20 ,  50 . 
         [0026]    In use, the inner tubular member  20  and the outer tubular member  50  are subjected to relative axial and radial deflections, due to vibrations and thermal growth variations, as well as sizing and positioning manufacturing tolerances. For these reasons, the inner tubular member  20  and outer tubular member  50  are relatively sized to allow a range of relative angular displacement therebetween. As seen in  FIGS. 5 and 6 , the outer peripheral surface  48  of the ring  40  has a curved profile or rounded contour, which extends between the opposed radial annular side walls  42  along the longitudinal direction  44 . When the tubular members  20 ,  50  are subjected to relative angular deflections, the rounded contour of the outer peripheral surface  48  of the ring  40  allows the inner tubular member  20  to roll, by way of the ring  40 , along the inner surface  52  of the outer tubular member  50 , while maintaining the ring  40  abutted to the outer tubular member  50 . The curved profile is configured to provide continuous abutment of the outer peripheral surface  48  on the inner surface  52  irrespective of angular displacement of the cylindrical adaptor relative to the cylindrical conduit. The rounded contour decreases the wear on the outer tubular member  50  and provides for uniform wear on the outer peripheral surface  48  of the ring. In this particular embodiment, the rounded contour of the outer peripheral surface  48  is only slightly curved. The curved profile of the outer peripheral surface  48  defines a radius of curvature R (see  FIG. 5 ) and the ratio between the radius of curvature and the outer diameter  60  of the ring  40  is within the range of 0.02 to 0.08. 
         [0027]    Furthermore, the gap  38  between the ring  40  and the circumferential surface  36  of the groove  30  allows for relative displacement of the ring  40  inside the groove  30 . When subjected to certain axial or angular deflections, the ring  40  may therefore completely fill a portion of the groove  30  at a first angular position while still protruding therefrom, while at another angular position, the gap  38  is present between the ring  40  and the circumferential surface  36 , with a greater portion of the ring protruding from the groove  30 . When subjected to different axial or angular deflections, the gap  38  may be located at a different angular position along the circumference of the groove  30 . This provides the transfer tube assembly  8 ,  8 ′ with a greater degree of flexibility when subjected to axial or angular loads, which decreases the wear caused to the assembly  8 ,  8 ′. 
         [0028]    The transfer tube assembly  8 ,  8 ′ reduces the wear on the inner tubular member  20  and the outer tubular member  50  by using the ring  40  as the sole contact between these two components. In addition, the transfer tube assembly  8 ,  8 ′ allows for the sealed connection to be maintained when subjected to axial or angular deflections, vibration loads or when exposed to high temperatures. 
         [0029]    In an alternate embodiment shown in  FIG. 7 , the circumferential surface  36  at the bottom of the groove  30  comprises holes  74  defined therein in fluid communication with a source of pressurized air  76 . This pressurized air  76  may be bleed air or may be additional air from the compressor. The pressurized air  76  pressurizes the groove  30  such as to press the ring  40  against the outer tubular member  50 , in order to improve the sealing connection therebetween. 
         [0030]    In another alternate embodiment shown in  FIG. 8 , the outer peripheral surface  148  of the ring  140  has a curved profile or rounded contour which includes two curves  80 ,  82 , in side by side relationship along a longitudinal direction between the opposed annular walls  142  of the ring  140 , with each curve  80 ,  82  having a respective different radius of curvature R 1 , R 2 . Such a contour provides for additional rolling capability of the inner tubular member  20  on the outer tubular member  50 , by way of the ring  140 , thereby further limiting wear and reinforcing the sealing therein. In a particular embodiment, the two different profiles may be defined along portions of the cross-section of the ring have different widths and/or heights from one another. In another embodiment (not shown), the outer peripheral surface of the ring may have a curved profile or rounded contour with more than two distinct curves. 
         [0031]    The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. For example, although the transfer tube assembly  8 ,  8 ′ is described as being used in a gas turbine engine bleed air system, the transfer tube assembly could also be used in any type of system where fluid is transferred by pipe or tube. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.