US20090067917A1 - Bipod Flexure Ring - Google Patents

Bipod Flexure Ring Download PDF

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Publication number
US20090067917A1
US20090067917A1 US11/851,622 US85162207A US2009067917A1 US 20090067917 A1 US20090067917 A1 US 20090067917A1 US 85162207 A US85162207 A US 85162207A US 2009067917 A1 US2009067917 A1 US 2009067917A1
Authority
US
United States
Prior art keywords
frame
thermal expansion
thermal coupling
thermal
flange
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.)
Abandoned
Application number
US11/851,622
Other languages
English (en)
Inventor
William P. Keith
Michael L. Hand
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Priority to US11/851,622 priority Critical patent/US20090067917A1/en
Assigned to THE BOEING COMPANY reassignment THE BOEING COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HAND, MICHAEL L., KEITH, WILLIAM P.
Priority to CA2638187A priority patent/CA2638187C/en
Priority to JP2008213978A priority patent/JP5317581B2/ja
Priority to EP08163806.6A priority patent/EP2034135B1/en
Publication of US20090067917A1 publication Critical patent/US20090067917A1/en
Priority to US12/783,599 priority patent/US8328453B2/en
Priority to US13/649,770 priority patent/US8834056B2/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/90—Mounting on supporting structures or systems
    • F05B2240/92—Mounting on supporting structures or systems on an airbourne structure
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/50—Flanged connections
    • F16B2200/506—Flanged connections bolted or riveted
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.
    • Y10T403/217—Members having different coefficients of expansion

Definitions

  • the present disclosure is generally directed to a thermal coupling.
  • An illustrative embodiment of the thermal coupling includes a first structure having a first coefficient of thermal expansion; a second structure having a second coefficient of thermal expansion lower than the first coefficient of thermal expansion; a plurality of thermal expansion fingers provided in the first structure; a plurality of thermal expansion flanges extending from the plurality of thermal expansion fingers, respectively; and a flange extending from the second structure and attached to the plurality of thermal expansion flanges.
  • thermal coupling includes an attachment frame; a plurality of frame ribs extending from the attachment frame; a plurality of fastener rings provided on the plurality of frame ribs, respectively; and a plurality of fastener ring openings provided in the plurality of fastener rings, respectively.
  • FIG. 1 is a partial sectional perspective view of an illustrative embodiment of the thermal coupling, attaching a structure having a high CTE to a structure having a low CTE.
  • FIG. 2 is an end view of the low CTE structure side of the thermal coupling.
  • FIG. 3 is an end view of the high CTE structure side of the thermal coupling.
  • FIG. 4 is a side view of an illustrative embodiment of the thermal coupling and the high CTE structure and the low CTE structure connected via the thermal coupling.
  • FIG. 5 is a perspective sectional view of an alternative illustrative embodiment of the thermal coupling, attached to an aircraft engine nozzle (partially in section).
  • FIG. 6 is a front view of the alternative illustrative embodiment of the thermal coupling illustrated in FIG. 5 .
  • FIG. 8 is a block diagram of an aircraft.
  • the thermal coupling 1 may couple a structure having a relatively high CTE (coefficient of thermal expansion) 2 to a structure having a relatively low CTE 14 and facilitate relative thermal expansion and retraction of the high CTE structure 2 with respect to the low CTE structure 14 during cyclic heating and cooling of the thermal coupling 1 .
  • the high CTE structure 2 may be a metal such as titanium, for example, and may include a high CTE wall 3 which defines a structure interior 4 ( FIG. 3 ).
  • the low CTE structure 14 may be ceramic and may include a low CTE wall 15 which defines a structure interior 16 .
  • the high CTE structure 2 has a coefficient of thermal expansion (CTE) which is higher than that of the low CTE structure 14 .
  • the thermal coupling 1 may include multiple generally elongated, parallel thermal expansion slots 7 which extend through the high CTE wall 3 of the high CTE structure 2 .
  • the thermal expansion slots 7 may be disposed in generally parallel, spaced-apart relationship with respect to each other around the circumference of the high CTE structure 2 .
  • the longitudinal axis of each thermal expansion slot 7 may be oriented in generally parallel relationship with respect to a longitudinal axis of the high CTE structure 2 .
  • a thermal expansion finger 7 a may be defined between each pair of adjacent thermal expansion slots 7 .
  • Thermal expansion flanges 8 may extend from the respective thermal expansion fingers 7 a. Each thermal expansion flange 8 may be oriented in generally perpendicular relationship with respect to the corresponding thermal expansion finger 7 a from which the thermal expansion flange 8 extends. As shown in FIG. 3 , each thermal expansion flange 8 may have a pair of scalloped or beveled flange edges 8 a. A flange slot 9 may be defined between each adjacent pair of thermal expansion flanges 8 . As further shown in FIG. 3 , a fastener opening 10 may extend through each thermal expansion flange 8 for purposes which will be hereinafter described.
  • An annular flange 18 ( FIG. 2 ), which may be continuous, may extend from the low CTE wall 15 of the low CTE structure 14 .
  • the flange 18 may be oriented in generally perpendicular relationship with respect to the longitudinal axis of the low CTE structure 14 .
  • Multiple, spaced-apart fastener openings 19 may extend through the flange 18 .
  • the fastener openings 19 may correspond in number and position to the fastener openings 10 provided in the respective thermal expansion flanges 8 on the high CTE structure 2 . As shown in FIG.
  • flange fasteners 20 may extend through the fastener openings 19 in the flange 18 and the registering fastener openings 10 in the thermal expansion flanges 8 , respectively, to attach the low CTE structure 14 to the high CTE structure 2 .
  • the thermal coupling 21 is a scalloped ring or spaceframe structure including an attachment frame 22 which may be a material having a relatively high CTE (coefficient of thermal expansion).
  • the attachment frame 22 is a metal such as titanium, for example.
  • the attachment frame 22 may include an annular frame ring 23 .
  • Multiple, spaced-apart fastener openings 24 (one of which is shown in FIG. 5 ) may extend through the frame ring 23 .
  • An annular frame flange 26 may extend from the frame ring 23 , in generally perpendicular relationship with respect to the frame ring 23 .
  • Multiple, spaced-apart fastener openings 27 may extend through the frame flange 26 .
  • each frame rib 30 may extend from the attachment frame 22 in generally adjacent, spaced-apart relationship with respect to each other.
  • Each frame rib 30 may include a pair of generally elongated rib members 33 which converge distally toward each other as they extend from the attachment frame 22 .
  • Each rib member 33 of each frame rib 30 may be oriented in generally parallel relationship with respect to the frame ring 23 and in generally perpendicular relationship with respect to the frame flange 26 of the attachment frame 22 .
  • a fastener ring 31 may be provided on the converging distal ends of the rib members 33 .
  • a fastener ring opening 32 may extend through each fastener ring 31 .
  • the thermal coupling 21 connects a first structure (not shown) having a high CTE (coefficient of thermal expansion) to a second structure 44 having a relatively low CTE.
  • the high CTE structure is attached to the high CTE attachment frame 22
  • the low CTE structure 44 is attached to the fastener rings 31 of the frame ribs 30 .
  • the frame flange 26 on the high CTE attachment frame 22 may be attached to the high CTE structure by extending fasteners (not shown) through fastener openings (not shown) provided in the high CTE structure and through the registering fastener openings 27 provided in the frame flange 26 .
  • the fastener ring 31 on each pair of converging rib members 33 may be attached to the low CTE structure 44 by extending a rib fastener 34 through a rib fastener opening 49 provided in the low CTE structure 44 and through a registering fastener ring opening 32 provided in the fastener ring 31 .
  • a seal strip 36 may be provided between the frame ring 23 of the high CTE attachment frame 22 and the fastener rings 31 on the frame ribs 30 .
  • the relatively high CTE structure thermally expands relative to the relatively low CTE structure 44 .
  • the frame ribs 30 of the thermal coupling 21 facilitate radial and axial expansion of the high CTE structure relative to the low CTE structure 44 without the application of thermally-induced stresses to the low CTE structure 44 .
  • the thermal coupling 21 may be capable of withstanding shear loads directed at right angles with respect to the center axis of the thermal coupling 21 as well as fore and aft loads which are directed parallel to the central axis of the thermal coupling 21 . Therefore, thermal stresses between the high CTE structure and the low CTE structure 44 during thermal cycling is minimized, thus substantially preventing any possible change in the low CTE structure 44 in cases in which the low CTE structure 44 is ceramic.
  • embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 78 as shown in FIG. 7 and an aircraft 94 as shown in FIG. 8 .
  • exemplary method 78 may include specification and design 80 of the aircraft 94 and material procurement 82 .
  • component and subassembly manufacturing 84 and system integration 86 of the aircraft 94 takes place.
  • the aircraft 94 may go through certification and delivery 88 in order to be placed in service 90 .
  • routine maintenance and service 90 (which may also include modification, reconfiguration, refurbishment, and so on).
  • Each of the processes of method 78 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer).
  • a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors
  • a third party may include without limitation any number of vendors, subcontractors, and suppliers
  • an operator may be an airline, leasing company, military entity, service organization, and so on.
  • the aircraft 94 produced by exemplary method 78 may include an airframe 98 with a plurality of systems 96 and an interior 100 .
  • high-level systems 96 include one or more of a propulsion system 102 , an electrical system 104 , a hydraulic system 106 , and an environmental system 108 . Any number of other systems may be included.
  • an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the automotive industry.
  • the apparatus embodied herein may be employed during any one or more of the stages of the production and service method 78 .
  • components or subassemblies corresponding to production process 84 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 94 is in service.
  • one or more apparatus embodiments may be utilized during the production stages 84 and 86 , for example, by substantially expediting assembly of or reducing the cost of an aircraft 94 .
  • one or more apparatus embodiments may be utilized while the aircraft 94 is in service, for example and without limitation, to maintenance and service 92 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Connection Of Plates (AREA)
  • Flanged Joints, Insulating Joints, And Other Joints (AREA)
  • Joints Allowing Movement (AREA)
  • Clamps And Clips (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
US11/851,622 2007-09-07 2007-09-07 Bipod Flexure Ring Abandoned US20090067917A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US11/851,622 US20090067917A1 (en) 2007-09-07 2007-09-07 Bipod Flexure Ring
CA2638187A CA2638187C (en) 2007-09-07 2008-08-01 Bipod flexure ring
JP2008213978A JP5317581B2 (ja) 2007-09-07 2008-08-22 熱継手
EP08163806.6A EP2034135B1 (en) 2007-09-07 2008-09-05 Bipod flexure ring
US12/783,599 US8328453B2 (en) 2007-09-07 2010-05-20 Bipod flexure ring
US13/649,770 US8834056B2 (en) 2007-09-07 2012-10-11 Bipod flexure ring

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/851,622 US20090067917A1 (en) 2007-09-07 2007-09-07 Bipod Flexure Ring

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/783,599 Division US8328453B2 (en) 2007-09-07 2010-05-20 Bipod flexure ring

Publications (1)

Publication Number Publication Date
US20090067917A1 true US20090067917A1 (en) 2009-03-12

Family

ID=40111025

Family Applications (3)

Application Number Title Priority Date Filing Date
US11/851,622 Abandoned US20090067917A1 (en) 2007-09-07 2007-09-07 Bipod Flexure Ring
US12/783,599 Active US8328453B2 (en) 2007-09-07 2010-05-20 Bipod flexure ring
US13/649,770 Active US8834056B2 (en) 2007-09-07 2012-10-11 Bipod flexure ring

Family Applications After (2)

Application Number Title Priority Date Filing Date
US12/783,599 Active US8328453B2 (en) 2007-09-07 2010-05-20 Bipod flexure ring
US13/649,770 Active US8834056B2 (en) 2007-09-07 2012-10-11 Bipod flexure ring

Country Status (4)

Country Link
US (3) US20090067917A1 (enExample)
EP (1) EP2034135B1 (enExample)
JP (1) JP5317581B2 (enExample)
CA (1) CA2638187C (enExample)

Cited By (5)

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US20090064681A1 (en) * 2007-09-07 2009-03-12 The Boeing Company Scalloped Flexure Ring
US20100227698A1 (en) * 2007-09-07 2010-09-09 The Boeing Company Bipod Flexure Ring
US20100316437A1 (en) * 2009-06-16 2010-12-16 Utah State University Research Foundation Thermal Expansion Compensation Method and System
US20130051897A1 (en) * 2011-08-23 2013-02-28 Bae Systems Information And Electronic Systems Integration Inc. Rigid adaptor ring for cte mismatched optical device components
US20140219707A1 (en) * 2013-02-07 2014-08-07 Rolls-Royce Plc Panel mounting arrangement

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US9764849B2 (en) 2014-09-18 2017-09-19 The Boeing Company Method of attaching nacelle structure to minimize fatigue loading
US10801729B2 (en) 2015-07-06 2020-10-13 General Electric Company Thermally coupled CMC combustor liner
US9856011B2 (en) * 2015-08-06 2018-01-02 The Boeing Company Method for the joining of wings or control surfaces to an airplane fuselage
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US10168051B2 (en) 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US10197278B2 (en) 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US10837640B2 (en) 2017-03-06 2020-11-17 General Electric Company Combustion section of a gas turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
FR3084916B1 (fr) * 2018-08-10 2020-07-17 Safran Ceramics Cone d'ejection a fixation flexible
US11767770B2 (en) 2021-08-10 2023-09-26 The Boeing Company Double bipod fitting to mitigate thermal loading of engine exhaust structures
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US20130034378A1 (en) 2013-02-07
JP5317581B2 (ja) 2013-10-16
EP2034135B1 (en) 2014-08-13
CA2638187A1 (en) 2009-03-07
US8328453B2 (en) 2012-12-11
JP2009063166A (ja) 2009-03-26
CA2638187C (en) 2011-10-11
US20100227698A1 (en) 2010-09-09
EP2034135A2 (en) 2009-03-11
US8834056B2 (en) 2014-09-16
EP2034135A3 (en) 2012-04-18

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