US20140138945A1 - Tube having an integral, spring-loaded, spherical joint - Google Patents
Tube having an integral, spring-loaded, spherical joint Download PDFInfo
- Publication number
- US20140138945A1 US20140138945A1 US13/681,734 US201213681734A US2014138945A1 US 20140138945 A1 US20140138945 A1 US 20140138945A1 US 201213681734 A US201213681734 A US 201213681734A US 2014138945 A1 US2014138945 A1 US 2014138945A1
- Authority
- US
- United States
- Prior art keywords
- tube
- spring
- shoulder
- spherical
- secured
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000012530 fluid Substances 0.000 claims abstract description 59
- 230000013011 mating Effects 0.000 claims abstract description 25
- 239000011800 void material Substances 0.000 claims description 9
- 239000007789 gas Substances 0.000 description 26
- 239000000446 fuel Substances 0.000 description 15
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 230000035882 stress Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 230000002939 deleterious effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L27/00—Adjustable joints, Joints allowing movement
- F16L27/02—Universal joints, i.e. with mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction
- F16L27/04—Universal joints, i.e. with mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction with partly spherical engaging surfaces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L37/00—Couplings of the quick-acting type
- F16L37/08—Couplings of the quick-acting type in which the connection between abutting or axially overlapping ends is maintained by locking members
- F16L37/084—Couplings of the quick-acting type in which the connection between abutting or axially overlapping ends is maintained by locking members combined with automatic locking
- F16L37/088—Couplings of the quick-acting type in which the connection between abutting or axially overlapping ends is maintained by locking members combined with automatic locking by means of a split elastic ring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
- F05D2250/241—Three-dimensional ellipsoidal spherical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
Definitions
- the present disclosure relates to tubes for directing flow of fluids, and in particular relates to a tube having an integral, spring-loaded, spherical joint for permitting motion of portions of the tube relative to each other to minimize misalignment stresses to the tube while the tube is directing flow of extremely hot fluids under severe mechanical duress.
- a pilot assembly is utilized to direct flow of flames through flame passages into an augmenter of a gas turbine engine.
- the flame passages dispense flames into a combustion section of the augmentor through openings that define a circumferential disposition around, a tail cone within the augmentor.
- a pilot combustor is located within the tail cone, and flames are directed from within the cone to the openings around the tail cone.
- the hot gases or flames from the flame passages of the pilot are utilized to efficiently ignite fuel within a combustion chamber of the augmentor when the fuel is injected into the combustion chamber through struts or vanes passing between the tail cone and an outer wall of the augmentor.
- the openings of the flame passages are defined immediately downstream from the fuel dispensing struts and the flames thereby serve to propagate an efficient combustion of the fuel within the augmentor.
- the flame passages of the pilot assembly may be formed by metallic tubes that direct flow of hot gases or flames from the pilot combustor to outlets defined around the tail cone within the augmentor. It has been found that such flame tubes are subject to extraordinary mechanical and thermal stresses as the augmentor is used to substantially enhance the thrust of the gas turbine engine, frequently propelling combustion products at supersonic speeds.
- U.S. Pat. No. 6,709,023 that issued on Mar. 23, 2004, to French discloses a “flexible slide joint” that provides for limited motion in a fluid conduit.
- French shows first and second tube members secured together by a sliding sealing sleeve member that houses an axially compressible element.
- One of the two members defines a spherical end portion that abuts an interior slide surface of the sealing sleeve member to provide the limited motion.
- the French disclosure requires complex manufacture, assembly and installation of many separate parts that utilise intricate components to secure the many parts as a single tube.
- the disclosure includes a tube having an integral, spring-loaded, spherical joint.
- the tube includes a first portion of the tube that has a first mating spherical section at an end of the first portion.
- a second portion of the tube has a second mating spherical section at an end of the second portion.
- the first and second mating spherical sections are secured adjacent each other to form a spherical joint configured to permit slidable rotational and angular motion between the first and second spherical sections and to prevent passage of fluid from an interior of the tube out of the tube between the spherical sections.
- the first portion includes a shoulder defined on the first portion a distance from the end of the first portion including the spherical section and in a direction toward an opposed end of the tube portion.
- the shoulder protrudes from the tube in a direction away from a fluid passage interior of the tube.
- the second portion of the tube includes a spring sleeve extending from the second spherical section toward the first tube portion, and the spring sleeve is configured to surround the shoulder on the end of the first portion of the tube.
- a spring is secured within the spring sleeve adjacent an exterior surface of the first portion and is secured between the shoulder and the spring sleeve. The spring asserts a spring-bias force to maintain the mating spherical sections of the tube portions in contact with each other.
- the tube may also have an end of one of the tube portions opposed to the spherical section ends that includes a telescope mount.
- the telescope mount at the end of the tube defines an expanded ring surrounding the end and the ring is configured to fit within a slide seal of the telescope mount.
- the slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the end so that fluid within the tube cannot pass between the slide seal and the expanded ring.
- the circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube.
- the second portion of the tube may be a discharge portion having the second spherical section adjacent an inlet end of the discharge portion and having an outlet end of the discharge portion of the tube secured to a flame port plate of a gas turbine engine.
- the discharge portion of the tube may also be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the first portion of the tube involves movement only of the first portion of the tube relative to the flame port plate.
- the tube having an integral spring-loaded, spherical joint may also be disclosed as having a fluid reception portion that has an inlet end and an opposed cylindrical outlet end, and that also has a fluid discharge portion having a cylindrical inlet end and an opposed outlet end.
- the cylindrical outlet end of the fluid reception portion of the tube defines a first spherical section surrounding the outlet end of the reception portion.
- the cylindrical inlet end of the fluid discharge portion of the tube defines a second mating spherical section surrounding the inlet end of the discharge portion.
- the second mating spherical section is configured to be secured to and overlie the first spherical section of the fluid reception portion to thereby permit slidable rotational and angular movement of the spherical sections adjacent each other and is also configured to prevent passage of fluid from within the tube through an interface between the spherical sections.
- the cylindrical outlet end of the reception portion of the tube defines a shoulder that is located a distance from the first spherical section.
- the shoulder extends from at least opposed sides of the outlet end of the tube and the shoulder protrudes from the tube in a direction away from a fluid passage interior of the tube.
- the shoulder defines a diameter between opposed perimeter edges of the shoulder.
- the cylindrical inlet end of the discharge portion of the tube defines a spring sleeve that extends from the second spherical section in a direction parallel to a direction of fluid flow through the discharge portion of the tube and that also extends toward the inlet end of the reception portion.
- the spring sleeve defines an interior void having a sleeve diameter that is greater than the shoulder diameter so that shoulder fits within the spring sleeve.
- the spring sleeve also defines an interior step at a bottom end of the spring sleeve, and the interior step extends into the interior void of the spring sleeve.
- the interior step is closer to the entry end of the reception portion of the tube than the shoulder defined on the reception portion of the tube.
- the interior step also defines a step diameter greater than the shoulder diameter and less than the sleeve diameter.
- a spring is secured within the spring sleeve adjacent an exterior surface of the reception portion and is also secured between the shoulder and the interior step of the spring sleeve for asserting a spring-bias force to maintain the mating spherical sections of the tube portions in contact with each other.
- the inlet end of the reception portion of the tube may include a telescope mount.
- the telescope mount defines an expanded ring surrounding the end and the ring is configured to fit within a slide seal of the telescope mount.
- the slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the end so that fluid within the tube cannot pass between the slide seal and the expanded ring.
- the circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube.
- the outlet end of the discharge portion of the tube may be secured to a flame port plate of a gas turbine engine. Additionally, the discharge portion of the tube may be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the reception portion of the tube involves movement only of the reception portion of the tube relative to the flame port plate.
- the tube may also include a compressible retaining clip configured to have a compressed outer diameter less than the step diameter of the spring sleeve and configured to have a non-compressed outer diameter greater than the step diameter and less than the shoulder diameter.
- the non-compressed retaining clip is secured adjacent the interior step within the spring sleeve so that the spring is secured between the retaining clip and the shoulder.
- the tube having an integral, spring-loaded, spherical joint may also be disclosed as including a first portion of the tube having a first mating spherical section at an end of the first portion, a second portion of the tube having a second mating spherical section at an end of the second portion, wherein the first and second mating spherical sections are secured adjacent each other to form a spherical joint configured to permit slidable, rotational and angular motion between the first and second spherical sections and to prevent passage of fluid from an interior of the tube out of the tube between the spherical sections.
- An end of one of the first and second portions opposed to the ends including one of the first and second spherical sections includes a telescope mount wherein the telescope mount end defines an expanded ring surrounding the end that is configured to fit within a slide seal of the telescope mount.
- the slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the telescope mount end so that fluid within the tube cannot pass between the slide seal and the expanded ring.
- the circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube.
- a telescope mount spring sleeve extends away from the slide seal of the telescope mount in a direction of the fluid flow through the tube.
- the telescope mount spring sleeve defines a base step that extends toward the tube portion from the spring sleeve to form a wall of the slide seal.
- a shoulder is defined on the telescope mount end between the expanded ring and the end having the spherical section. The shoulder extends away from an interior of the tube portion, and the shoulder defines a diameter that is less than a diameter of the telescope mount spring sleeve so that the spring sleeve overlies the shoulder.
- a spring is secured adjacent an exterior surface of the telescope mount end and between the base step and the shoulder to force the shoulder away from the base step, and to thereby maintain the spherical sections of the tube portions in contact with each other.
- the second portion of the tube may be a discharge portion having the second spherical section adjacent an inlet end of the discharge portion and having an outlet end of the discharge portion of the tube secured to a flame port plate of a gas turbine engine.
- the discharge portion of the tube may be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the first portion of the tube involves movement only of the first portion of the tube relative to the flame port plate.
- At least one of the first portion or the second portion of the tube may also include an exterior wall surrounding the first and/or second portions.
- the exterior wall defines a void between the exterior wall and the first portion and/or the second portion of the tube.
- FIG. 1 is a simplified schematic drawing showing twin spool axial flow gas turbine engine with an augmentor, or after-burner
- FIG. 2 is simplified, fragmentary schematic drawing showing a burner section of a gas turbine engine augmentor, which is a working environment of the present invention.
- FIG. 3 is a cross-sectional view of a tube having an integral, spring-loaded, spherical joint constructed in accordance with the present invention.
- FIG. 4 is fragmentary, expanded view of the FIG. 3 tube, showing an expanded view of mating spherical sections or portions of the tube forming a spherical joint, showing a spring sleeve encasing a shoulder of an outlet end of a reception portion of the tube, and showing a spring within the spring sleeve secured between a shoulder of the outlet end and a retaining clip secured adjacent an interior step of the spring sleeve.
- FIG. 5 is a perspective view of a wave spring suitable for use in the tube having an integral, spring-loaded, spherical joint.
- FIG. 6 is a cross-sectional, fragmentary view of a telescope mount spring sleeve embodiment of the tube showing a spring sleeve extending from a slide seal of a telescope mount of the tube, and showing the spring sleeve overlying a shoulder defined above the inlet end of the reception portion of the tube.
- FIG. 1 shows a simplified, schematic representation of a preferred working environment for the present disclosure; namely a gas turbine engine generally designated by the reference numeral 10 .
- the engine 10 includes a hollow engine casing 12 which includes a variety of components and engine modules (not shown) that are not pertinent to the present disclosure.
- a low pressure fan/compressor section 14 interconnected by a shaft 16 to a low pressure turbine 18 which drives the compressor 14 .
- a second shaft 20 is connected to a high pressure turbine 22 which drives a high pressure compressor section 24 .
- An annular burner 26 is disposed between the high pressure compressor 24 and the high pressure turbine 22 , and the burner 26 serves to combust fuel so that a portion of the energy extracted from hot combusted accelerated gases powers the turbines which drive the compressors, while remaining energy of the combusted gases produces thrust for driving the gas turbine engine 10 in a desired direction.
- An augmentor 28 is located downstream from the low pressure turbine 18 and is used to substantially augment thrust of the engine by directing fuel into the stream of combusted gases.
- Downstream from the low pressure turbine 18 is a tail cone 32 and a plurality of inlet diffusers 34 , 35 that extend from the tail cone 32 to a concentrically space inner liner 36 that serve to direct and stabilize flow of combusted gases discharged from the burner 26 after the gases pass through the turbines 18 , 22 .
- vanes 38 , 39 extend from the tail cone 32 to the inner liner 36 in parallel alignment with and rearward of the inlet, diffuser 34 .
- the vanes 38 , 39 provide passageways for fuel entering the augmentor 28 as described in more detail below.
- a plurality of flame ports 40 surrounds the tail cone 32 , and the flame ports 40 are defined to be adjacent bottom edges of vanes 38 , 39 .
- FIG. 2 shows a fragmentary, expanded view of an inlet diff user 34 of FIG. 1 that includes a strut 42 .
- a passageway 46 directs flow of combusted gases from downstream of the turbines 18 , 22 into the augmentor 28 .
- Fuel apertures 50 on the downstream side of the strut 42 dispense fuel into gases passing through the passageway
- FIG. 2 also shows a flame port plate 52 that defines an exemplary flame port 54 through which a flame (not shown) passes to ignite any fuel passing through the fuel apertures 50 .
- a flame (not shown) passes to ignite any fuel passing through the fuel apertures 50 .
- Shown also in FIG. 2 is a simplified view of a tube 60 of the present invention secured to the flame port plate 52 .
- An arrow 62 shown passing through the tube 60 indicates an axis of and a direction of fluid flow through the tube.
- the tube 60 is also secured to a support 64 .
- the present tube 60 having an integral, spring-loaded, spherical joint minimises deleterious effects of such duress on the tube 60 and also minimizes any misalignment of flow of flames through the flame port plate 52 by permitting limited angular, rotational and axial movement between a reception portion 66 of the tube 60 and a discharge portion 63 of the tube 60 .
- FIG. 3 shows a cross-sectional view of the tube 60 having an integral, spring-loaded, spherical joint constructed in accordance with the present disclosure.
- the tube 60 includes the fluid reception 66 or first portion 66 of the tube 60 , and the fluid reception portion 66 has an inlet end 70 and an opposed cylindrical outlet end 72 .
- a fluid discharge portion 68 or second portion 68 has a cylindrical inlet end 74 and an opposed outlet end 76 .
- the outlet end 76 of the discharge portion 68 also includes a mounting bracket 78 defining at least one bolt throughbore 80 for securing the discharge portion 68 to the flame port plate 52 .
- the cylindrical outlet end 72 of the fluid reception portion 66 of the tube 60 defines a first spherical section 82 surrounding the outlet end 72 of the reception portion 66 of the tube 60 .
- the first spherical section 82 may be convex, or alternatively may foe concave (not shown).
- the first spherical section 82 may also be defined on the opposite or inlet end 70 or the reception portion 66 of the tube.
- the cylindrical inlet end 74 of the fluid discharge portion 68 of the tube 60 defines a second spherical section 84 surrounding the inlet end 74 of the discharge portion 68 of the tube 60 .
- the first spherical section 82 and the second spherical section 84 may also include wear surfaces that may foe separable (not shown) and seal pieces (not shown) between the sections 82 , 84 that enhance longevity of the spherical sections 82 , 84 and minimize any fluid leaking between the sections 82 , 84 .
- FIG. 3 shows the second spherical section 84 as concave, but it may be convex (not shown).
- first spherical section 82 and the second spherical section 84 define mating or different spherical section surfaces configured to prevent passage of fluids between the surfaces 82 , 84 whenever the spherical section 82 , 84 are in intimate contact with each other, while the spherical sections 82 , 84 are secured in slidable association with each other.
- the two spherical sections 82 , 84 form a spherical joint 86 that is integral with the tube 60 .
- the concave or second spherical section 84 (shown in FIG. 3 ) is configured to be secured to and to overlie the first or convex spherical section 82 of the fluid reception portion 66 to thereby permit slidable movement of the spherical sections 82 , 84 adjacent each other.
- the spherical sections 82 , 84 are configured to also prevent passage of fluid from within the tube through an interface of the spherical sections 82 , 84 of the tube.
- the cylindrical outlet end 72 of the first or reception portion 66 of the tube defines a shoulder 88 below (wherein “below” is in a direction toward the inlet end 70 of the reception portion 66 ) the convex spherical section 82 shown in FIG. 3 .
- the shoulder 88 extends from at least opposed sides of the outlet end 72 , and may include a plurality of shoulder tabs (not shown) or a surrounding shoulder 88 .
- the shoulder 88 protrudes from the outlet end 72 of the reception portion 66 of the tube 60 in a direction away from a fluid passage interior 90 of the tube 60 , and the shoulder 88 defines a shoulder diameter between opposed perimeter edges of the shoulder 88 .
- the cylindrical inlet end 74 of the discharge 68 or second portion of the tube 60 defines a spring sleeve 92 that extends from the concave or second spherical section 84 and extends in a direction toward the entry end 70 of the reception portion 66 of the tube 60 .
- the spring sleeve 92 defines an interior void 94 having a sleeve diameter greater than the shoulder diameter so that, shoulder 83 of the outlet end 72 of the reception portion 66 fits within the spring sleeve 92 . As best shown in FIG.
- the spring sleeve 92 defines an interior step 96 at a bottom end 98 of the spring sleeve 92 , and the step 96 extends into the interior void 94 of the spring sleeve 92 .
- the interior step 96 defines a step diameter that is greater than the shoulder diameter and that, is less than the sleeve diameter.
- the interior step 96 is closer to the entry end 70 of the reception portion 66 than is the shoulder 88 defined on the reception portion 66 of the tube 60 .
- a compressible retaining clip 100 is configured to have a compressed outer diameter less than the step diameter and is configured to have a non-compressed outer diameter greater than the step diameter and an inner diameter less than the shoulder diameter.
- the retaining clip 100 may be compressed to fit within the spring sleeve 92 , and then it may be expanded so that the retaining clip 100 sits on the step 96 of the spring sleeve 92 , but cannot pass over the shoulder 88 at the outlet end 72 of the reception portion 66 of the tube 60 .
- the non-compressed retaining clip 100 is secured adjacent the interior step 96 within the spring sleeve 92 .
- a spring such as a “wave spring” 102 shown alone in FIG.
- a standard coil spring (not shown) is secured between the retaining clip 100 and the shoulder 88 .
- the spring 102 is configured to assert a spring-bias force between the shoulder 88 and the non-compressed retaining clip 100 to thereby force and maintain the spherical section 82 of the outlet end 72 of the reception portion 66 of the tube 60 against the mating spherical section 84 of the inlet end 74 of the discharge portion 68 of the tube 60 .
- FIGS. 3 and 4 show the retaining clip 100 , shoulder 83 and spring 102 therebetween as the integral spring-loaded portion of the tube 60 , it is to be understood that any spring loading that is integral with (meaning mechanically connected to and forming a part of the tube 60 ) may also be utilized.
- the compressible retaining clip 100 provides an efficient mechanism for securing the spring 102 between the shoulder 88 and the step 96
- alternative spring securing mechanisms may be utilized, such as the spring sleeve 92 defining screw threads or projecting tabs and a retainer being screwed into the spring sleeve 92 or a notched washer being positioned upon the projecting tabs, etc.
- the spring-loaded aspect of the tube 60 will be broadly characterised as a spring 102 secured within the spring sleeve 92 between the shoulder 88 of a first portion of the tube 60 and the spring sleeve 92 of a second portion of the tube 60 for asserting a spring-bias force to draw the spherical sections 82 , 84 of the tube portions toward each other.
- the shoulder 38 may be defined a sufficient distance away from the spherical section 82 at the outlet end 72 of the reception portion 66 of the tube 60 so that a displacement region 104 is defined between the shoulder 88 and the spherical section 82 .
- a displacement void 106 is defined between the shoulder 88 and the spherical section 82 .
- the tube 60 may also include a telescope mount 110 wherein the inlet, end 70 of the reception portion 66 defines an expanded ring 112 surrounding the inlet end 70 and configured to fit within a slide seal 114 of the telescope mount 110 .
- the slide seal 114 defines a circumferential flange 116 dimensioned to receive the ring 112 of the inlet end 70 so that fluid within the tube 60 cannot pass between the slide seal 114 and the expanded ring 112 .
- the flange 116 is also dimensioned to permit the ring 112 to slide within the slide seal 114 in a direction parallel to an axis 62 of fluid flow through the inlet end 70 , thereby permitting sealed axial motion of the tube 60 along and parallel to the axis 62 of fluid flow through the tube 60 .
- FIG. 3 shows that the telescope mount 110 portion of the tube 60 includes a securing extension 117 for securing the telescope mount 110 and tube 60 to the support 64 , such as by a standard screw and bolt mechanism 118 .
- FIG. 3 also shows that the support 64 may also define a flame outlet tunnel 119 for directing flame out of the combustor (not shown), through the tunnel 119 and into the tube 60 .
- the flame outlet tunnel 119 may be inserted into the telescope mount 110 , or into the inlet end 70 of the reception portion 66 of the tube 60 .
- the inlet end 70 of the reception portion 66 of the tube 60 is secured to the support 64 (shown in FIG. 2 ) of an adjacent pilot combustor (not shown) so that flames from the pilot combustor pass from the inlet end 70 of the reception portion 66 of the tube 60 and pass out of the outlet end 76 of the discharge portion 68 of the tube 60 .
- the outlet end 76 of the discharge portion 68 of the tube 60 may be secured in rigid association with the flame port plate 52 adjacent an exterior surface of the tail cone 32 within the augmentor 28 of the gas turbine engine 10 . This permits flames or extremely hot gases to pass out of the tube 60 and through the flame port 54 into the augmentor 28 .
- any angular, rotational or axial movement, between the discharge portion 68 and the reception portion 66 and/or the telescoping end 110 of the tube 60 exclusively involves movement of the reception portion 66 of the tube 60 relative to the flame port plate 52 .
- the tube 60 may be secured to the flame port plate 52 so that an axis of fluid flow out of the discharge portion 68 of the tube 60 through the flame port 54 is always the same, while the reception portion 66 of the tube 60 experiences limited movemen, relative to the flame port plate 52 .
- a second spring sleeve 142 may extend away from a slide seal 114 ′′′ of the telescope mount 110 ′′ in a direction of the fluid flow through the tube 60 ′′.
- the inlet end 70 ′′ or telescope mount end 70 ′′ of the reception portion 68 ′′ of the tube 140 may define an inlet-end shoulder 144 , similar to the shoulder 88 described above, so that the inlet-end shoulder 144 extends at least from opposed sides of the inlet end 70 ′′ of the reception portion 66 ′′ of the tube 140 .
- the inlet-end shoulder 144 defines an inlet-end shoulder 144 diameter that is less than a diameter of the telescope mount spring sleeve 142 so that, the spring sleeve 142 may overlie the inlet-end shoulder 144 .
- the telescope mount spring sleeve tube 140 defines a base step 146 extending toward the tube 140 from the spring sleeve 142 to a wall of the slide seal 114 ′′.
- a second spring 148 is secured between the base step 146 and the inlet-end shoulder 144 to force the shoulder 144 away from the base step 146 , and to thereby force the spherical section 82 of the outlet end 72 of the reception portion 66 (shown in FIG.
- the telescope mount spring sleeve embodiment of the tube 140 also describes a joint 86 having an integral second spring 148 .
- the telescope mount spring sleeve tube embodiment 140 does not require usage of the spring 102 between the spherical sections 82 , 84 because the second spring 148 achieves the same function of the spring 102 of applying a securing force to maintain the spherical sections 82 , 84 in intimate, fluid-sealing contact with each other.
- the present inventive tubes 60 , 140 having an integral, spring-loaded, spherical joint 86 provide for efficient manufacture, assembly and installation of the tubes 60 , 140 , in particular within very constrained working environments, such as along with a plurality of identical or similar tubes within or adjacent,the tail cone 32 of a gas turbine engine 10 .
- tubes 60 , 140 having integral, spring-loaded, spherical joints 86
- the disclosure is not to be limited to those alternatives and described embodiments.
- the tubes 60 , 140 are disclosed primarily with respect, to the working environment of a gas turbine engine 10 , however the tubes 60 , 140 may be utilized in alternative working environments wherein fluid flow directing tube are exposed to extremes of thermal and mechanical duress. Accordingly, reference should be made primarily to the following claims rather than the foregoing description to determine the scope of the disclosure.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Joints Allowing Movement (AREA)
Abstract
Description
- This disclosure was made with Government support under contract number N0019-02-C-3003 awarded by The United States Navy. The Government has certain rights in this disclosure.
- The present disclosure relates to tubes for directing flow of fluids, and in particular relates to a tube having an integral, spring-loaded, spherical joint for permitting motion of portions of the tube relative to each other to minimize misalignment stresses to the tube while the tube is directing flow of extremely hot fluids under severe mechanical duress.
- In the field of aircraft engine technology, it is well known that extremely hot fluids and combusting fuel mixtures are directed to flow through varying types of conduits ranging from tubes to augmentors, or after-burner sections of gas turbine engines. As disclosed in U.S. Pat. No. 5,385,015 that issued on Jan. 31, 1995 to Clements et al., which Patent is owned by the owner of all rights in the present disclosure, a pilot assembly is utilized to direct flow of flames through flame passages into an augmenter of a gas turbine engine. The flame passages dispense flames into a combustion section of the augmentor through openings that define a circumferential disposition around, a tail cone within the augmentor. A pilot combustor is located within the tail cone, and flames are directed from within the cone to the openings around the tail cone.
- The hot gases or flames from the flame passages of the pilot are utilized to efficiently ignite fuel within a combustion chamber of the augmentor when the fuel is injected into the combustion chamber through struts or vanes passing between the tail cone and an outer wall of the augmentor. The openings of the flame passages are defined immediately downstream from the fuel dispensing struts and the flames thereby serve to propagate an efficient combustion of the fuel within the augmentor.
- The flame passages of the pilot assembly may be formed by metallic tubes that direct flow of hot gases or flames from the pilot combustor to outlets defined around the tail cone within the augmentor. It has been found that such flame tubes are subject to extraordinary mechanical and thermal stresses as the augmentor is used to substantially enhance the thrust of the gas turbine engine, frequently propelling combustion products at supersonic speeds.
- Many efforts have been undertaken to produce fluid conduits that provide for limited movement within the conduit to compensate for axial, rotational and angular stresses. For example, published European Patent Application No. EP 0919774 A3 published on Jun. 2, 1999 shows a “flame tube inter connector” that, discloses a joint, providing limited movement. The joint includes a first transfer tube having a seat that mates with a spherical or conical seat of a second transfer tube. A spring is included within one of the tubes to draw the two tubes into contact with each other, and exterior flanges include complex throughbores for flexibly bolting the tubes together. While providing for limited axial, radial and rotational motion at the joint, this disclosure exposes the spring to rapid wear by being within the tubes, and the bolting mechanism requires complicated manufacture and installation complexities.
- More recently, U.S. Pat. No. 6,709,023 that issued on Mar. 23, 2004, to French discloses a “flexible slide joint” that provides for limited motion in a fluid conduit. French shows first and second tube members secured together by a sliding sealing sleeve member that houses an axially compressible element. One of the two members defines a spherical end portion that abuts an interior slide surface of the sealing sleeve member to provide the limited motion. Like Clements et al., the French disclosure requires complex manufacture, assembly and installation of many separate parts that utilise intricate components to secure the many parts as a single tube.
- Therefore, there is a need for a tube having a joint that provides for limited angular, rotational and axial movement between portions of the tube while tolerating flow through the tube of extremely hot fluids and experiencing severe mechanical duress associated with supersonic gas turbine engines.
- The disclosure includes a tube having an integral, spring-loaded, spherical joint. The tube includes a first portion of the tube that has a first mating spherical section at an end of the first portion. A second portion of the tube has a second mating spherical section at an end of the second portion. The first and second mating spherical sections are secured adjacent each other to form a spherical joint configured to permit slidable rotational and angular motion between the first and second spherical sections and to prevent passage of fluid from an interior of the tube out of the tube between the spherical sections. The first portion includes a shoulder defined on the first portion a distance from the end of the first portion including the spherical section and in a direction toward an opposed end of the tube portion. The shoulder protrudes from the tube in a direction away from a fluid passage interior of the tube. The second portion of the tube includes a spring sleeve extending from the second spherical section toward the first tube portion, and the spring sleeve is configured to surround the shoulder on the end of the first portion of the tube. A spring is secured within the spring sleeve adjacent an exterior surface of the first portion and is secured between the shoulder and the spring sleeve. The spring asserts a spring-bias force to maintain the mating spherical sections of the tube portions in contact with each other.
- The tube may also have an end of one of the tube portions opposed to the spherical section ends that includes a telescope mount. The telescope mount at the end of the tube defines an expanded ring surrounding the end and the ring is configured to fit within a slide seal of the telescope mount. The slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the end so that fluid within the tube cannot pass between the slide seal and the expanded ring. The circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube.
- The second portion of the tube may be a discharge portion having the second spherical section adjacent an inlet end of the discharge portion and having an outlet end of the discharge portion of the tube secured to a flame port plate of a gas turbine engine. The discharge portion of the tube may also be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the first portion of the tube involves movement only of the first portion of the tube relative to the flame port plate.
- The tube having an integral spring-loaded, spherical joint may also be disclosed as having a fluid reception portion that has an inlet end and an opposed cylindrical outlet end, and that also has a fluid discharge portion having a cylindrical inlet end and an opposed outlet end. The cylindrical outlet end of the fluid reception portion of the tube defines a first spherical section surrounding the outlet end of the reception portion. The cylindrical inlet end of the fluid discharge portion of the tube defines a second mating spherical section surrounding the inlet end of the discharge portion. The second mating spherical section is configured to be secured to and overlie the first spherical section of the fluid reception portion to thereby permit slidable rotational and angular movement of the spherical sections adjacent each other and is also configured to prevent passage of fluid from within the tube through an interface between the spherical sections. The cylindrical outlet end of the reception portion of the tube defines a shoulder that is located a distance from the first spherical section. The shoulder extends from at least opposed sides of the outlet end of the tube and the shoulder protrudes from the tube in a direction away from a fluid passage interior of the tube. The shoulder defines a diameter between opposed perimeter edges of the shoulder. The cylindrical inlet end of the discharge portion of the tube defines a spring sleeve that extends from the second spherical section in a direction parallel to a direction of fluid flow through the discharge portion of the tube and that also extends toward the inlet end of the reception portion. The spring sleeve defines an interior void having a sleeve diameter that is greater than the shoulder diameter so that shoulder fits within the spring sleeve. The spring sleeve also defines an interior step at a bottom end of the spring sleeve, and the interior step extends into the interior void of the spring sleeve. The interior step is closer to the entry end of the reception portion of the tube than the shoulder defined on the reception portion of the tube. The interior step also defines a step diameter greater than the shoulder diameter and less than the sleeve diameter.
- A spring is secured within the spring sleeve adjacent an exterior surface of the reception portion and is also secured between the shoulder and the interior step of the spring sleeve for asserting a spring-bias force to maintain the mating spherical sections of the tube portions in contact with each other.
- The inlet end of the reception portion of the tube may include a telescope mount. The telescope mount defines an expanded ring surrounding the end and the ring is configured to fit within a slide seal of the telescope mount. The slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the end so that fluid within the tube cannot pass between the slide seal and the expanded ring. The circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube.
- The outlet end of the discharge portion of the tube may be secured to a flame port plate of a gas turbine engine. Additionally, the discharge portion of the tube may be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the reception portion of the tube involves movement only of the reception portion of the tube relative to the flame port plate.
- The tube may also include a compressible retaining clip configured to have a compressed outer diameter less than the step diameter of the spring sleeve and configured to have a non-compressed outer diameter greater than the step diameter and less than the shoulder diameter. The non-compressed retaining clip is secured adjacent the interior step within the spring sleeve so that the spring is secured between the retaining clip and the shoulder.
- The tube having an integral, spring-loaded, spherical joint may also be disclosed as including a first portion of the tube having a first mating spherical section at an end of the first portion, a second portion of the tube having a second mating spherical section at an end of the second portion, wherein the first and second mating spherical sections are secured adjacent each other to form a spherical joint configured to permit slidable, rotational and angular motion between the first and second spherical sections and to prevent passage of fluid from an interior of the tube out of the tube between the spherical sections. An end of one of the first and second portions opposed to the ends including one of the first and second spherical sections includes a telescope mount wherein the telescope mount end defines an expanded ring surrounding the end that is configured to fit within a slide seal of the telescope mount. The slide seal defines a circumferential flange that is dimensioned to receive the expanded ring of the telescope mount end so that fluid within the tube cannot pass between the slide seal and the expanded ring. The circumferential flange is also dimensioned to permit the expanded ring to slide within the slide seal in a direction parallel to an axis of fluid flow through the tube. Also, a telescope mount spring sleeve extends away from the slide seal of the telescope mount in a direction of the fluid flow through the tube. The telescope mount spring sleeve defines a base step that extends toward the tube portion from the spring sleeve to form a wall of the slide seal. A shoulder is defined on the telescope mount end between the expanded ring and the end having the spherical section. The shoulder extends away from an interior of the tube portion, and the shoulder defines a diameter that is less than a diameter of the telescope mount spring sleeve so that the spring sleeve overlies the shoulder. A spring is secured adjacent an exterior surface of the telescope mount end and between the base step and the shoulder to force the shoulder away from the base step, and to thereby maintain the spherical sections of the tube portions in contact with each other.
- The second portion of the tube may be a discharge portion having the second spherical section adjacent an inlet end of the discharge portion and having an outlet end of the discharge portion of the tube secured to a flame port plate of a gas turbine engine.
- The discharge portion of the tube may be secured in rigid association with the flame port plate so that any angular, rotational or axial movement between the discharge portion and the first portion of the tube involves movement only of the first portion of the tube relative to the flame port plate.
- At least one of the first portion or the second portion of the tube may also include an exterior wall surrounding the first and/or second portions. The exterior wall defines a void between the exterior wall and the first portion and/or the second portion of the tube.
- Accordingly, it is a general purpose of the present disclosure to provide a tube having an integral, spring-loaded spherical joint that overcomes deficiencies of the prior art.
- It is a more specific purpose of the present disclosure to provide a tube having an integral, spring-loaded spherical joint that enhances efficiencies of manufacture, assembly and installation of the tube within complex working environments, and that provides a flame tube having a longer useful life and greater resistance to failure than known flame tubes in similar working environments. These and other purposes and values of the present disclosure will become apparent in the following detailed description and the accompanying drawings.
-
FIG. 1 is a simplified schematic drawing showing twin spool axial flow gas turbine engine with an augmentor, or after-burner -
FIG. 2 is simplified, fragmentary schematic drawing showing a burner section of a gas turbine engine augmentor, which is a working environment of the present invention. -
FIG. 3 is a cross-sectional view of a tube having an integral, spring-loaded, spherical joint constructed in accordance with the present invention. -
FIG. 4 is fragmentary, expanded view of theFIG. 3 tube, showing an expanded view of mating spherical sections or portions of the tube forming a spherical joint, showing a spring sleeve encasing a shoulder of an outlet end of a reception portion of the tube, and showing a spring within the spring sleeve secured between a shoulder of the outlet end and a retaining clip secured adjacent an interior step of the spring sleeve. -
FIG. 5 is a perspective view of a wave spring suitable for use in the tube having an integral, spring-loaded, spherical joint. -
FIG. 6 is a cross-sectional, fragmentary view of a telescope mount spring sleeve embodiment of the tube showing a spring sleeve extending from a slide seal of a telescope mount of the tube, and showing the spring sleeve overlying a shoulder defined above the inlet end of the reception portion of the tube. - Referring to the drawings in detail,
FIG. 1 shows a simplified, schematic representation of a preferred working environment for the present disclosure; namely a gas turbine engine generally designated by thereference numeral 10. Theengine 10 includes ahollow engine casing 12 which includes a variety of components and engine modules (not shown) that are not pertinent to the present disclosure. Within theengine casing 12 is a low pressure fan/compressor section 14 interconnected by a shaft 16 to a low pressure turbine 18 which drives thecompressor 14. Asecond shaft 20 is connected to a high pressure turbine 22 which drives a high pressure compressor section 24. Anannular burner 26 is disposed between the high pressure compressor 24 and the high pressure turbine 22, and theburner 26 serves to combust fuel so that a portion of the energy extracted from hot combusted accelerated gases powers the turbines which drive the compressors, while remaining energy of the combusted gases produces thrust for driving thegas turbine engine 10 in a desired direction. - An
augmentor 28, or after-burner, is located downstream from the low pressure turbine 18 and is used to substantially augment thrust of the engine by directing fuel into the stream of combusted gases. Downstream from the low pressure turbine 18 is atail cone 32 and a plurality ofinlet diffusers tail cone 32 to a concentrically spaceinner liner 36 that serve to direct and stabilize flow of combusted gases discharged from theburner 26 after the gases pass through the turbines 18, 22. Finally,vanes tail cone 32 to theinner liner 36 in parallel alignment with and rearward of the inlet,diffuser 34. Thevanes augmentor 28 as described in more detail below. A plurality offlame ports 40 surrounds thetail cone 32, and theflame ports 40 are defined to be adjacent bottom edges ofvanes -
FIG. 2 shows a fragmentary, expanded view of aninlet diff user 34 ofFIG. 1 that includes astrut 42. Apassageway 46 directs flow of combusted gases from downstream of the turbines 18, 22 into theaugmentor 28. Fuel apertures 50 on the downstream side of thestrut 42 dispense fuel into gases passing through the passageway -
FIG. 2 also shows aflame port plate 52 that defines anexemplary flame port 54 through which a flame (not shown) passes to ignite any fuel passing through the fuel apertures 50. Shown also inFIG. 2 is a simplified view of atube 60 of the present invention secured to theflame port plate 52. Anarrow 62 shown passing through thetube 60 indicates an axis of and a direction of fluid flow through the tube. Thetube 60 is also secured to asupport 64. - Whenever the fuel apertures 50 dispense fuel in the
augmentor 28, flames passing from a combustor (not shown) adjacent thesupport 64 pass through thetube 60 arid through theflame port 54 to ignite the fuel. This creates extraordinary thermal and mechanical duress on all components of thegas turbine engine 10, and especially on theflame port plate 54 and thetube 60 secured thereto. As described in detail below, thepresent tube 60 having an integral, spring-loaded, spherical joint minimises deleterious effects of such duress on thetube 60 and also minimizes any misalignment of flow of flames through theflame port plate 52 by permitting limited angular, rotational and axial movement between areception portion 66 of thetube 60 and a discharge portion 63 of thetube 60. -
FIG. 3 shows a cross-sectional view of thetube 60 having an integral, spring-loaded, spherical joint constructed in accordance with the present disclosure. Thetube 60 includes thefluid reception 66 orfirst portion 66 of thetube 60, and thefluid reception portion 66 has aninlet end 70 and an opposedcylindrical outlet end 72. Afluid discharge portion 68 orsecond portion 68 has acylindrical inlet end 74 and anopposed outlet end 76. Theoutlet end 76 of thedischarge portion 68 also includes a mountingbracket 78 defining at least onebolt throughbore 80 for securing thedischarge portion 68 to theflame port plate 52. - The cylindrical outlet end 72 of the
fluid reception portion 66 of thetube 60 defines a firstspherical section 82 surrounding the outlet end 72 of thereception portion 66 of thetube 60. As shown inFIG. 3 , the firstspherical section 82 may be convex, or alternatively may foe concave (not shown). The firstspherical section 82 may also be defined on the opposite orinlet end 70 or thereception portion 66 of the tube. Thecylindrical inlet end 74 of thefluid discharge portion 68 of thetube 60 defines a secondspherical section 84 surrounding theinlet end 74 of thedischarge portion 68 of thetube 60. The firstspherical section 82 and the secondspherical section 84 may also include wear surfaces that may foe separable (not shown) and seal pieces (not shown) between thesections spherical sections sections FIG. 3 shows the secondspherical section 84 as concave, but it may be convex (not shown). It is necessary, however, that the firstspherical section 82 and the secondspherical section 84 define mating or different spherical section surfaces configured to prevent passage of fluids between thesurfaces spherical section spherical sections spherical sections tube 60. - Again and for clarity, the concave or second spherical section 84 (shown in
FIG. 3 ) is configured to be secured to and to overlie the first or convexspherical section 82 of thefluid reception portion 66 to thereby permit slidable movement of thespherical sections spherical sections spherical sections - The cylindrical outlet end 72 of the first or
reception portion 66 of the tube defines ashoulder 88 below (wherein “below” is in a direction toward theinlet end 70 of the reception portion 66) the convexspherical section 82 shown inFIG. 3 . Theshoulder 88 extends from at least opposed sides of theoutlet end 72, and may include a plurality of shoulder tabs (not shown) or a surroundingshoulder 88. Theshoulder 88 protrudes from the outlet end 72 of thereception portion 66 of thetube 60 in a direction away from afluid passage interior 90 of thetube 60, and theshoulder 88 defines a shoulder diameter between opposed perimeter edges of theshoulder 88. - The
cylindrical inlet end 74 of thedischarge 68 or second portion of thetube 60 defines aspring sleeve 92 that extends from the concave or secondspherical section 84 and extends in a direction toward theentry end 70 of thereception portion 66 of thetube 60. Thespring sleeve 92 defines aninterior void 94 having a sleeve diameter greater than the shoulder diameter so that, shoulder 83 of the outlet end 72 of thereception portion 66 fits within thespring sleeve 92. As best shown inFIG. 4 , thespring sleeve 92 defines aninterior step 96 at abottom end 98 of thespring sleeve 92, and thestep 96 extends into theinterior void 94 of thespring sleeve 92. Theinterior step 96 defines a step diameter that is greater than the shoulder diameter and that, is less than the sleeve diameter. Theinterior step 96 is closer to theentry end 70 of thereception portion 66 than is theshoulder 88 defined on thereception portion 66 of thetube 60. - as best shown in
FIG. 4 , acompressible retaining clip 100 is configured to have a compressed outer diameter less than the step diameter and is configured to have a non-compressed outer diameter greater than the step diameter and an inner diameter less than the shoulder diameter. As described above, the retainingclip 100 may be compressed to fit within thespring sleeve 92, and then it may be expanded so that the retainingclip 100 sits on thestep 96 of thespring sleeve 92, but cannot pass over theshoulder 88 at the outlet end 72 of thereception portion 66 of thetube 60. Thenon-compressed retaining clip 100 is secured adjacent theinterior step 96 within thespring sleeve 92. A spring, such as a “wave spring” 102 shown alone inFIG. 5 , or a standard coil spring (not shown) is secured between the retainingclip 100 and theshoulder 88. Thespring 102 is configured to assert a spring-bias force between theshoulder 88 and thenon-compressed retaining clip 100 to thereby force and maintain thespherical section 82 of the outlet end 72 of thereception portion 66 of thetube 60 against the matingspherical section 84 of theinlet end 74 of thedischarge portion 68 of thetube 60. - While
FIGS. 3 and 4 show the retainingclip 100, shoulder 83 andspring 102 therebetween as the integral spring-loaded portion of thetube 60, it is to be understood that any spring loading that is integral with (meaning mechanically connected to and forming a part of the tube 60) may also be utilized. For example, while thecompressible retaining clip 100 provides an efficient mechanism for securing thespring 102 between theshoulder 88 and thestep 96, alternative spring securing mechanisms may be utilized, such as thespring sleeve 92 defining screw threads or projecting tabs and a retainer being screwed into thespring sleeve 92 or a notched washer being positioned upon the projecting tabs, etc. For purposes herein, therefore, the spring-loaded aspect of thetube 60 will be broadly characterised as aspring 102 secured within thespring sleeve 92 between theshoulder 88 of a first portion of thetube 60 and thespring sleeve 92 of a second portion of thetube 60 for asserting a spring-bias force to draw thespherical sections - As also best shown in
FIG. 4 , theshoulder 38 may be defined a sufficient distance away from thespherical section 82 at the outlet end 72 of thereception portion 66 of thetube 60 so that adisplacement region 104 is defined between theshoulder 88 and thespherical section 82. As thespring sleeve 92 overlies theshoulder 88 and outlet end 72 of thespherical section 82, a displacement void 106 is defined between theshoulder 88 and thespherical section 82. As the concavespherical section 84 of theinlet end 74 of thedischarge portion 68 of thetube 60 slides adjacent the mating convexspherical section 82 of the outlet end 72 of thereception portion 66 of thetube 60, some of the concavespherical section 84 moves into the displacement void 106 to thereby permit slidable motion of thespherical sections - As shown in
FIG. 3 , thetube 60 may also include atelescope mount 110 wherein the inlet, end 70 of thereception portion 66 defines an expandedring 112 surrounding theinlet end 70 and configured to fit within aslide seal 114 of thetelescope mount 110. Theslide seal 114 defines acircumferential flange 116 dimensioned to receive thering 112 of theinlet end 70 so that fluid within thetube 60 cannot pass between theslide seal 114 and the expandedring 112. Theflange 116 is also dimensioned to permit thering 112 to slide within theslide seal 114 in a direction parallel to anaxis 62 of fluid flow through theinlet end 70, thereby permitting sealed axial motion of thetube 60 along and parallel to theaxis 62 of fluid flow through thetube 60.FIG. 3 shows that thetelescope mount 110 portion of thetube 60 includes a securingextension 117 for securing thetelescope mount 110 andtube 60 to thesupport 64, such as by a standard screw andbolt mechanism 118.FIG. 3 also shows that thesupport 64 may also define aflame outlet tunnel 119 for directing flame out of the combustor (not shown), through thetunnel 119 and into thetube 60. Theflame outlet tunnel 119 may be inserted into thetelescope mount 110, or into theinlet end 70 of thereception portion 66 of thetube 60. - In an ordinary working environment of the integral, spring-loaded spherical
joint tube 60, such as thegas turbine engine 10 described above, theinlet end 70 of thereception portion 66 of thetube 60 is secured to the support 64 (shown inFIG. 2 ) of an adjacent pilot combustor (not shown) so that flames from the pilot combustor pass from theinlet end 70 of thereception portion 66 of thetube 60 and pass out of the outlet end 76 of thedischarge portion 68 of thetube 60. As described with respect toFIG. 2 , the outlet end 76 of thedischarge portion 68 of thetube 60 may be secured in rigid association with theflame port plate 52 adjacent an exterior surface of thetail cone 32 within theaugmentor 28 of thegas turbine engine 10. This permits flames or extremely hot gases to pass out of thetube 60 and through theflame port 54 into theaugmentor 28. - By having the
discharge portion 68 secured in rigid association with theflame port plate 52, it is meant that any angular, rotational or axial movement, between thedischarge portion 68 and thereception portion 66 and/or thetelescoping end 110 of thetube 60 exclusively involves movement of thereception portion 66 of thetube 60 relative to theflame port plate 52. In other words, while thetube 60 provides for movement between thedischarge portion 68 andreception portion 66, thetube 60 may be secured to theflame port plate 52 so that an axis of fluid flow out of thedischarge portion 68 of thetube 60 through theflame port 54 is always the same, while thereception portion 66 of thetube 60 experiences limited movemen, relative to theflame port plate 52. - As shown in
FIG. 6 , in a further alternative telescope mount springsleeve tube embodiment 140, asecond spring sleeve 142 may extend away from aslide seal 114′″ of thetelescope mount 110″ in a direction of the fluid flow through thetube 60″. (In theFIG. 6 drawing, components that are virtually identical to components in theFIGS. 3 and 4 embodiments are shown with reference numerals that are double primes of theFIGS. 3 and 4 reference numerals. For example, inFIG. 6 , theFIG. 3 telescope mount 110 is shown as 110″.) Additionally, theinlet end 70″ or telescope mount end 70″ of thereception portion 68″ of thetube 140 may define an inlet-end shoulder 144, similar to theshoulder 88 described above, so that the inlet-end shoulder 144 extends at least from opposed sides of theinlet end 70″ of thereception portion 66″ of thetube 140. - The inlet-
end shoulder 144 defines an inlet-end shoulder 144 diameter that is less than a diameter of the telescopemount spring sleeve 142 so that, thespring sleeve 142 may overlie the inlet-end shoulder 144. The telescope mountspring sleeve tube 140 defines abase step 146 extending toward thetube 140 from thespring sleeve 142 to a wall of theslide seal 114″. Asecond spring 148 is secured between thebase step 146 and the inlet-end shoulder 144 to force theshoulder 144 away from thebase step 146, and to thereby force thespherical section 82 of the outlet end 72 of the reception portion 66 (shown inFIG. 3 ) of thetube 140 into intimate contact with thespherical section 84 of theinlet end 74 of the discharge portion 68 (shown inFIG. 3 ) of thetube 140. Because thesecond spring 148 is encased within the telescopemount spring sleeve 142 of thetube 140, the telescope mount spring sleeve embodiment of thetube 140 also describes a joint 86 having an integralsecond spring 148. In particular working environments, being able to slide theinlet end 70″ of thereception portion 66″ of thetube 140 into the telescopemount spring sleeve 142 facilitates assembly, and dispenses with any need to compress aretainer clip 100 to secure thesecond spring 148 within thespring sleeve 142 in the assembly process and/or installation process. It is to be understood that the telescope mount springsleeve tube embodiment 140 does not require usage of thespring 102 between thespherical sections second spring 148 achieves the same function of thespring 102 of applying a securing force to maintain thespherical sections - The present
inventive tubes tubes tail cone 32 of agas turbine engine 10. - All patents, published patent applications and related patent documents referred to in this document are incorporated herein by reference thereto.
- While the above disclosure has been presented with respect to the described and illustrated embodiments of
tubes spherical joints 86, it is to be understood that the disclosure is not to be limited to those alternatives and described embodiments. For example, thetubes gas turbine engine 10, however thetubes
Claims (12)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/681,734 US8733800B1 (en) | 2012-11-20 | 2012-11-20 | Tube having an integral, spring-loaded, spherical joint |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/681,734 US8733800B1 (en) | 2012-11-20 | 2012-11-20 | Tube having an integral, spring-loaded, spherical joint |
Publications (2)
Publication Number | Publication Date |
---|---|
US20140138945A1 true US20140138945A1 (en) | 2014-05-22 |
US8733800B1 US8733800B1 (en) | 2014-05-27 |
Family
ID=50727229
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/681,734 Expired - Fee Related US8733800B1 (en) | 2012-11-20 | 2012-11-20 | Tube having an integral, spring-loaded, spherical joint |
Country Status (1)
Country | Link |
---|---|
US (1) | US8733800B1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3082912A1 (en) * | 2018-06-25 | 2019-12-27 | Safran Aircraft Engines | FLUIDIC CONNECTION DEVICE FOR AN AIR CIRCUIT OF AN AIRCRAFT ENGINE |
US11400329B2 (en) * | 2017-05-02 | 2022-08-02 | Minimax Gmbh | Connection adapter for a container for a fire-extinguishing agent pertaining to a fire-extinguishing system |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10625871B1 (en) * | 2015-08-24 | 2020-04-21 | Roller Bearing Company Of America, Inc. | Dynamic movement tube connection system |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US99003A (en) * | 1870-01-18 | Improvement in pipe-coupling for heating cars | ||
USRE23298E (en) * | 1950-11-28 | Swing joint | ||
US918144A (en) * | 1908-04-25 | 1909-04-13 | Greenlaw Mfg Company | Flexible pipe-joint. |
US1202502A (en) * | 1912-02-10 | 1916-10-24 | Charles Forth | Pipe-joint. |
US1434631A (en) * | 1921-01-22 | 1922-11-07 | James J Reynolds | Flexible pipe joint |
US1915100A (en) * | 1933-01-20 | 1933-06-20 | Milton P Mclaughlin | Flexible conduit |
US2616728A (en) | 1948-02-20 | 1952-11-04 | Solar Aircraft Co | Flexible exhaust pipe joint |
US2840394A (en) * | 1952-02-14 | 1958-06-24 | Rohr Aircraft Corp | Flexible joint engine exhaust duct with bellows seal |
US2693971A (en) * | 1952-10-20 | 1954-11-09 | Harrison Wesley | Ball-and-socket pipe coupling |
US3047315A (en) * | 1960-02-05 | 1962-07-31 | Western Piping & Engineering C | Spring urged ball and socket exhaust pipe connector |
FR2199844A5 (en) | 1972-09-15 | 1974-04-12 | Snecma | |
US4054306A (en) | 1976-05-28 | 1977-10-18 | Pressure Science Incorporated | Tube and cylindrical surface sealing apparatus |
JPS59131722A (en) * | 1983-01-17 | 1984-07-28 | Mazda Motor Corp | Structure of exhaust pipe of engine for vehicle |
US4641861A (en) * | 1984-06-01 | 1987-02-10 | O.E.M. Technical Sales, Inc. | Flexible joint for pipes |
US4570440A (en) * | 1985-07-02 | 1986-02-18 | Chrysler Corporation | Articulated connector |
FR2629863B1 (en) | 1988-04-12 | 1991-02-08 | Dubois Jacques | FLEXIBLE EXHAUST COUPLING |
US5335947A (en) * | 1990-02-05 | 1994-08-09 | Preece Incorporated | Quick disconnect ball joint coupling |
US5209428A (en) | 1990-05-07 | 1993-05-11 | Lockheed Corporation | Propulsion system for a vertical and short takeoff and landing aircraft |
US5385015A (en) | 1993-07-02 | 1995-01-31 | United Technologies Corporation | Augmentor burner |
JP2001050457A (en) | 1999-08-03 | 2001-02-23 | Smc Corp | Tube joint |
US6709023B2 (en) * | 2002-01-11 | 2004-03-23 | Perkinelmer Inc. | Flexible slide joint |
US7784835B1 (en) * | 2006-12-05 | 2010-08-31 | Keays Steven J | Pipe connecting member |
-
2012
- 2012-11-20 US US13/681,734 patent/US8733800B1/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11400329B2 (en) * | 2017-05-02 | 2022-08-02 | Minimax Gmbh | Connection adapter for a container for a fire-extinguishing agent pertaining to a fire-extinguishing system |
FR3082912A1 (en) * | 2018-06-25 | 2019-12-27 | Safran Aircraft Engines | FLUIDIC CONNECTION DEVICE FOR AN AIR CIRCUIT OF AN AIRCRAFT ENGINE |
Also Published As
Publication number | Publication date |
---|---|
US8733800B1 (en) | 2014-05-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10550767B2 (en) | Gas turbine engine recuperator with floating connection | |
US20110089266A1 (en) | Fuel nozzle lip seals | |
US10196975B2 (en) | Turboprop engine with compressor turbine shroud | |
RU2470169C2 (en) | Turbo machine with diffuser | |
US6439616B1 (en) | Anti-rotation retainer for a conduit | |
CN113623023B (en) | Pressure regulating piston seal for a gas turbine combustor liner | |
US8662502B2 (en) | Fuel nozzle seal spacer and method of installing the same | |
CA2570777C (en) | Internally mounted device for a gas turbine engine | |
US20160356223A1 (en) | Igniter assembly for a gas turbine engine | |
US10422533B2 (en) | Combustor with axially staged fuel injector assembly | |
US6401447B1 (en) | Combustor apparatus for a gas turbine engine | |
CN105042636B (en) | Fuel delivery system | |
US10781710B2 (en) | Sealing configuration to reduce air leakage | |
US11085633B2 (en) | Nozzle with insulating air gap and seal to close the gap | |
EP3597869B1 (en) | Sealing configuration for a transfer tube assembly to reduce air leakage | |
US8733800B1 (en) | Tube having an integral, spring-loaded, spherical joint | |
JP2008122068A (en) | Combustor dome mixer retaining means | |
US5390498A (en) | Fuel distribution assembly | |
US10294865B2 (en) | Internal manifold with fuel inlet | |
CN109386840B (en) | Volute combustor for gas turbine engine | |
JP7212431B2 (en) | Combustion dynamics mitigation system | |
US11662096B2 (en) | Combustor swirler to pseudo-dome attachment and interface with a CMC dome | |
CN107250673A (en) | Combustion liner flexible support and method | |
US20180363913A1 (en) | Assembly of tube and structure crossing multi chambers | |
US8083940B2 (en) | Oil strainer for a gas turbine engine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:RUBERTE SANCHEZ, JOSE E.;HANSON, RUSSELL B.;LOW, KEVIN J.;SIGNING DATES FROM 20121116 TO 20121119;REEL/FRAME:029328/0261 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551) Year of fee payment: 4 |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS Free format text: CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001 Effective date: 20200403 |
|
AS | Assignment |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION, CONNECTICUT Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:055659/0001 Effective date: 20200403 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20220527 |