WO2001026964A1 - Heat shield - Google Patents

Heat shield Download PDF

Info

Publication number
WO2001026964A1
WO2001026964A1 PCT/GB2000/003818 GB0003818W WO0126964A1 WO 2001026964 A1 WO2001026964 A1 WO 2001026964A1 GB 0003818 W GB0003818 W GB 0003818W WO 0126964 A1 WO0126964 A1 WO 0126964A1
Authority
WO
WIPO (PCT)
Prior art keywords
hot air
air duct
support member
aerofoil
shield
Prior art date
Application number
PCT/GB2000/003818
Other languages
French (fr)
Inventor
Timothy David James Wollaston
Original Assignee
Airbus Uk Limited
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 Airbus Uk Limited filed Critical Airbus Uk Limited
Priority to JP2001529997A priority Critical patent/JP2003511310A/en
Priority to AU75442/00A priority patent/AU7544200A/en
Publication of WO2001026964A1 publication Critical patent/WO2001026964A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/006—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being used to cool structural parts of the aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid

Definitions

  • the present invention relates to a heat shield, and in particular to a heat shield to deflect hot air away from the front spar of an aircraft aerofoil.
  • An Airbus aircraft usually has metallic spars within its aerofoil. Heat shields are attached to the spars using fasteners, and are usually individually made to fit specific vent areas and, once fastened in place, tend to be awkward to remove. As a result, the shields also form part of the system installation for the aircraft.
  • the systems installation includes all the equipment used to run the aircraft, such as electrical circuitry and pneumatic, hydraulic and fuel components.
  • a heat shield for deflecting hot gases away from an aerofoil spar comprising a shield member, a support member for detachably supporting the shield member, and means for adjustably mounting the support member on a hot air duct positioned within an aircraft aerofoil, the arrangement being such that, in use, the heat shield can be positioned between the hot air duct and a spar of the aerofoil.
  • insulation is also provided between the hot air duct and the support member.
  • the insulation is made from material able to withstand the temperature of the exhaust gases, preferably a material such as aluminium or titanium.
  • the insulation may surround the hot air duct.
  • the support member may comprise a sleeve surrounding the insulator, in the form of a jubilee clip, whereby the support member is adjustably mounted on the insulator, and also constitutes the adjustable mounting means.
  • the shield member preferably, has an arcuate structure that is concentric with the hot abduct.
  • the shield member should have sufficient arc length, and should be adjustably positioned in such a way, as to ensure total deflection of all hot gases away from the front spar.
  • the arc length of the shield member may be sufficient so as to cross imaginary tangential lines between the hot air duct and each corner of the aerofoil spar.
  • the shield member is detachably attached to the support member by a fastener, and the shield member includes a receiving aperture through which to receive the fastener.
  • Figure 1 is a side view of an aerofoil of an aircraft; and Figure 2 is a side expanded view of the D-nose assembly section of Figure 1, showing the hot air duct and heat shield.
  • Figure 1 shows an aerofoil 1 of an aircraft, having a front spar 2 and a back spar 3.
  • the front spar 2 is made of carbon-reinforced plastics material, or from a similarly heat-resistant material.
  • the front spar 2 is situated at one end of the aerofoil 1, and defines a D-nose section 4 of the aerofoil.
  • a hot air duct 5 (see Figure 2) is situated within the D-nose section 4, between the front spar 2 and the leading edge of the aerofoil 1.
  • the hot air duct 5 must be capable of withstanding contained gases at a temperature greater than 230°C.
  • a wall 6 of insulative material surrounds the hot air duct 5.
  • An outer sleeve 7, in the form of a Jubilee clip surrounds the wall 6.
  • the outer sleeve 7 has two fasteners 8 attached thereto, and protruding therefrom.
  • the outer sleeve 7 also has a nozzle 9 formed on its surface.
  • the nozzle 9 is situated at the end of a vent 10 running through the wall 6.
  • a heat shield 11 is located between the hot air duct 5 and the front spar 2.
  • the heat shield 11 has an arcuate structure which is concentric with the hot air duct 5, and is positioned in such a way so as to deflect any hot gases, escaping from the hot air duct, in the event of fracture occurring in the wall of the hot air duct 5, via the vent 10 and the nozzle 9, away from the front spar 2.
  • the heat shield 11 has a respective aperture 12 located at each of its ends, the apertures receiving the fasteners 8 on the outer sleeve 7 of the hot air duct 5 in order to fix the heat shield in the required position over the vent 10.
  • the aerofoil 1 also holds the systems installation 13 of the aircraft. The systems installation 13 is located between the heat shield 1 1 and the front spar 2, and is thus protected from any hot air gases by the heat shield.
  • the heat shield 11 is made of a lightweight, heat-resistant material, preferably a material such as aluminium or titanium, and can be easily removed from the aerofoil 1 by unfastening the fasteners 8 attaching the heat shield to the outer sleeve 7 of the hot air duct 5. Furthermore, the position of the heat shield 11 can be adjusted to suit a variety of vent locations so that the front spar 2 and systems installation 13 remain protected from the hot gases. In order to place the heat shield 11 in the correct position over a given vent 10, the outer sleeve 7, in the form of a Jubilee clip, is rotated circumferentially around the hot air duct 5 so as to align the fasteners 8 attached thereto with the receiving apertures 12 in the heat shield 11.
  • the heat shield 11 must have a sufficient arc length in order to provide total protection to the front spar 2, i.e. by ensuring total deflection of hot gases bleeding from the nozzle 9. This length must also take into account the need for providing deflection of hot gases that may escape out of the hot air duct 5 from somewhere other than the nozzle 9, in the unlikely case of a duct fracture. Therefore, as can be clearly seen in Figure 2, the arc length of the heat shield 11 must cross the tangential lines between the hot air duct 5 and each comer of the front spar 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Insulation (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

Heat shield apparatus for deflecting hot gases away from an aerofoil spar (2). The apparatus comprises a shield member (11), a support member for detachably supporting the shield member, and means (8) for adjustably mounting the support member on a hot air duct (5) positioned within an aircraft aerofoil (1), the arrangement being such that, in use, the heat shield (11) can be positioned between the hot air duct (5) and the spar (2) of the aerofoil.

Description

Heat Shield
The present invention relates to a heat shield, and in particular to a heat shield to deflect hot air away from the front spar of an aircraft aerofoil.
It is an ongoing concern in the aviation industry that certain areas of aircraft remain protected from the intense heat of the hot air ducts through which exhaust gases flow from the jet engines, in particular, the spars within aerofoils, and more particularly the front spar nearest the hot air duct, which also forms part of the fuel tank boundary. In the event of a duct failure, the hot gases are directed out through vents strategically positioned within insulation material surrounding the hot air duct. The heat shield is positioned in such a way as to deflect the hot air away from the front spar.
An Airbus aircraft usually has metallic spars within its aerofoil. Heat shields are attached to the spars using fasteners, and are usually individually made to fit specific vent areas and, once fastened in place, tend to be awkward to remove. As a result, the shields also form part of the system installation for the aircraft. The systems installation includes all the equipment used to run the aircraft, such as electrical circuitry and pneumatic, hydraulic and fuel components.
Recently, there has been a tendency to make aerofoil spars of a lighter material such as carbon-reinforced plastics material. This material, however, is more prone to heat deformation than metal, and must be protected from hot gases to a greater extent. Furthermore, drilling of holes in the material, in order for the shield to be fastened to a spar, contributes to weakening of the structure and therefore any such drilling should be minimised as much as possible.
The present invention seeks to alleviate the disadvantages of current heat shields by providing a smaller, lighter heat shield that can be easily removed, adapted to suit different vent positions, and which does not interfere with the system installation. Accordingly, there is provided, a heat shield for deflecting hot gases away from an aerofoil spar, the heat shield comprising a shield member, a support member for detachably supporting the shield member, and means for adjustably mounting the support member on a hot air duct positioned within an aircraft aerofoil, the arrangement being such that, in use, the heat shield can be positioned between the hot air duct and a spar of the aerofoil.
Preferably, insulation is also provided between the hot air duct and the support member. The insulation is made from material able to withstand the temperature of the exhaust gases, preferably a material such as aluminium or titanium. The insulation may surround the hot air duct.
The support member may comprise a sleeve surrounding the insulator, in the form of a jubilee clip, whereby the support member is adjustably mounted on the insulator, and also constitutes the adjustable mounting means.
The shield member, preferably, has an arcuate structure that is concentric with the hot abduct. The shield member should have sufficient arc length, and should be adjustably positioned in such a way, as to ensure total deflection of all hot gases away from the front spar.
The arc length of the shield member may be sufficient so as to cross imaginary tangential lines between the hot air duct and each corner of the aerofoil spar.
Preferably still, the shield member is detachably attached to the support member by a fastener, and the shield member includes a receiving aperture through which to receive the fastener.
The present invention will now be described in detail, by way of example, with reference to the accompanying drawings, in which :
Figure 1 is a side view of an aerofoil of an aircraft; and Figure 2 is a side expanded view of the D-nose assembly section of Figure 1, showing the hot air duct and heat shield.
Referring to the drawings, Figure 1 shows an aerofoil 1 of an aircraft, having a front spar 2 and a back spar 3. The front spar 2 is made of carbon-reinforced plastics material, or from a similarly heat-resistant material. The front spar 2 is situated at one end of the aerofoil 1, and defines a D-nose section 4 of the aerofoil. A hot air duct 5 (see Figure 2) is situated within the D-nose section 4, between the front spar 2 and the leading edge of the aerofoil 1. The hot air duct 5 must be capable of withstanding contained gases at a temperature greater than 230°C. A wall 6 of insulative material surrounds the hot air duct 5. An outer sleeve 7, in the form of a Jubilee clip surrounds the wall 6. The outer sleeve 7 has two fasteners 8 attached thereto, and protruding therefrom. The outer sleeve 7 also has a nozzle 9 formed on its surface. The nozzle 9 is situated at the end of a vent 10 running through the wall 6. A heat shield 11 is located between the hot air duct 5 and the front spar 2.
The heat shield 11 has an arcuate structure which is concentric with the hot air duct 5, and is positioned in such a way so as to deflect any hot gases, escaping from the hot air duct, in the event of fracture occurring in the wall of the hot air duct 5, via the vent 10 and the nozzle 9, away from the front spar 2. The heat shield 11 has a respective aperture 12 located at each of its ends, the apertures receiving the fasteners 8 on the outer sleeve 7 of the hot air duct 5 in order to fix the heat shield in the required position over the vent 10. The aerofoil 1 also holds the systems installation 13 of the aircraft. The systems installation 13 is located between the heat shield 1 1 and the front spar 2, and is thus protected from any hot air gases by the heat shield.
The heat shield 11 is made of a lightweight, heat-resistant material, preferably a material such as aluminium or titanium, and can be easily removed from the aerofoil 1 by unfastening the fasteners 8 attaching the heat shield to the outer sleeve 7 of the hot air duct 5. Furthermore, the position of the heat shield 11 can be adjusted to suit a variety of vent locations so that the front spar 2 and systems installation 13 remain protected from the hot gases. In order to place the heat shield 11 in the correct position over a given vent 10, the outer sleeve 7, in the form of a Jubilee clip, is rotated circumferentially around the hot air duct 5 so as to align the fasteners 8 attached thereto with the receiving apertures 12 in the heat shield 11.
The heat shield 11 must have a sufficient arc length in order to provide total protection to the front spar 2, i.e. by ensuring total deflection of hot gases bleeding from the nozzle 9. This length must also take into account the need for providing deflection of hot gases that may escape out of the hot air duct 5 from somewhere other than the nozzle 9, in the unlikely case of a duct fracture. Therefore, as can be clearly seen in Figure 2, the arc length of the heat shield 11 must cross the tangential lines between the hot air duct 5 and each comer of the front spar 2.

Claims

Claims
1. Heat shield apparatus for deflecting hot gases away from an aerofoil spar, the apparatus comprising a shield member, a support member for detachably supporting the shield member, and means for adjustably mounting the support member on a hot air duct positioned within an aircraft aerofoil, the arrangement being such that, in use, the heat shield can be positioned between the hot air duct and a spar of the aerofoil.
2. Apparatus according to claim 1, further comprising insulation between the hot air duct and the support member.
3. Apparatus according to claim 2, wherein the insulator surrounds the hot air duct.
4. Apparatus according to claim 3, wherein the support member is a sleeve surrounding the insulator.
5. Apparatus according to claim 4, wherein the support member is in the form of a jubilee clip, whereby the support member is adjustably mounted on the insulator, and also constitutes the adjustable mounting means.
6. Apparatus according to any one of claims 1 to 5, wherein the shield member has an arcuate structure that is concentric with the hot air duct.
7. Apparatus according to claim 6, wherein the shield member has sufficient arc length, and is adjustably positioned in such a way, as to ensure total deflection of all hot gases away from the front spar.
8. Apparatus according to claim 7, wherein the arc length of the shield member is sufficient so as to cross imaginary tangential lines between the hot air duct and each corner of the aerofoil spar.
9. Apparatus according to any preceding claim, wherein the shield member is detachably attached to the support member by a fastener.
10. Apparatus according to claim 9, wherein the shield member includes a receiving aperture through which to receive the fastener.
PCT/GB2000/003818 1999-10-14 2000-10-06 Heat shield WO2001026964A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP2001529997A JP2003511310A (en) 1999-10-14 2000-10-06 Heat shield
AU75442/00A AU7544200A (en) 1999-10-14 2000-10-06 Heat shield

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9924228.1A GB9924228D0 (en) 1999-10-14 1999-10-14 A heat shield
GB9924228.1 1999-10-14

Publications (1)

Publication Number Publication Date
WO2001026964A1 true WO2001026964A1 (en) 2001-04-19

Family

ID=10862672

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2000/003818 WO2001026964A1 (en) 1999-10-14 2000-10-06 Heat shield

Country Status (4)

Country Link
JP (1) JP2003511310A (en)
AU (1) AU7544200A (en)
GB (1) GB9924228D0 (en)
WO (1) WO2001026964A1 (en)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2473387A (en) * 1947-05-28 1949-06-14 Curtiss Wright Corp Anti-icing means for aircraft
FR2040012A5 (en) * 1969-03-28 1971-01-15 Thermal Products Ltd
DE2327949A1 (en) * 1973-06-01 1974-12-19 Bremshey Ag DOUBLE WALL PIPE
US3863445A (en) * 1972-08-04 1975-02-04 Tenneco Inc Heat shields for exhaust system
US4085816A (en) * 1975-04-04 1978-04-25 Nissan Motor Co., Ltd. Heat shield for an exhaust tail pipe
US4358075A (en) * 1976-06-17 1982-11-09 Antonov Oleg K Anti-icing device for aerodynamic structures of aircraft
US4603824A (en) * 1983-08-12 1986-08-05 The Boeing Company Wing slat anti-ice air duct system with improved slide bearings and air seal
US4955193A (en) * 1989-07-17 1990-09-11 Custom Chrome, Inc. Adjustable shield for motorcycle exhaust pipe
DE19800167A1 (en) * 1997-01-08 1998-07-09 Volkswagen Ag High-temperature-proof conductor esp for installing in motor vehicles

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2473387A (en) * 1947-05-28 1949-06-14 Curtiss Wright Corp Anti-icing means for aircraft
FR2040012A5 (en) * 1969-03-28 1971-01-15 Thermal Products Ltd
US3863445A (en) * 1972-08-04 1975-02-04 Tenneco Inc Heat shields for exhaust system
DE2327949A1 (en) * 1973-06-01 1974-12-19 Bremshey Ag DOUBLE WALL PIPE
US4085816A (en) * 1975-04-04 1978-04-25 Nissan Motor Co., Ltd. Heat shield for an exhaust tail pipe
US4358075A (en) * 1976-06-17 1982-11-09 Antonov Oleg K Anti-icing device for aerodynamic structures of aircraft
US4603824A (en) * 1983-08-12 1986-08-05 The Boeing Company Wing slat anti-ice air duct system with improved slide bearings and air seal
US4955193A (en) * 1989-07-17 1990-09-11 Custom Chrome, Inc. Adjustable shield for motorcycle exhaust pipe
DE19800167A1 (en) * 1997-01-08 1998-07-09 Volkswagen Ag High-temperature-proof conductor esp for installing in motor vehicles

Also Published As

Publication number Publication date
AU7544200A (en) 2001-04-23
GB9924228D0 (en) 1999-12-15
JP2003511310A (en) 2003-03-25

Similar Documents

Publication Publication Date Title
US6983912B2 (en) Hybrid exhaust heat shield for pylon mounted gas turbine engines
US7900872B2 (en) Nacelle inlet thermal anti-icing spray duct support system
US6131855A (en) Device for removing hot air for a jet engine air inlet cowl with a de-icing circuit
US8662440B2 (en) AFT pylon fairing for an aircraft engine suspension system
US8777164B2 (en) Air intake structure for an aircraft nacelle
US5011098A (en) Thermal anti-icing system for aircraft
US7526921B2 (en) Auxiliary power unit with integral firebox
US7805949B2 (en) Device for supporting and housing auxiliaries in a bypass turbojet
EP0558726B1 (en) Thermal anti-icing of aircraft structures
EP2332835B1 (en) Single plane mount system for gas turbine engine
US8371522B2 (en) Device for cooling hot gas to be discharged from an aircraft
US3779006A (en) Flame shield for a gas turbine engine
EP2894096B1 (en) Aircraft anti-icing systems having deflector vanes
US6435452B1 (en) Aircraft drainmast assembly
US5976997A (en) Lightweight fire protection arrangement for aircraft gas turbine jet engine and method
EP3031733B1 (en) Fire containment apparatuses for aircraft duct assemblies
US20100102172A1 (en) Aircraft structure
US20140263837A1 (en) Nacelle inlet thermal anti-ice spray duct
US6241189B1 (en) Protective device for a jet engine air inlet cowl equipped with a deicing system
EP3048257B1 (en) Electric conduction structure for jet engine
WO2001026964A1 (en) Heat shield
US20060032974A1 (en) Modular installation kit for auxiliary power unit
JP7160580B2 (en) Aircraft and aircraft maintenance methods
CN210942312U (en) Gas rudder assembly
US20100269328A1 (en) Device for mechanically decoupled fastening of an aircraft component perfused by hot gas

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 09700414

Country of ref document: US

ENP Entry into the national phase

Ref country code: JP

Ref document number: 2001 529997

Kind code of ref document: A

Format of ref document f/p: F

AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CR CU CZ DE DK DM DZ EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ PL PT RO RU SD SE SG SI SK SL TJ TM TR TT TZ UA UG US UZ VN YU ZA ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE BF BJ CF CG CI CM GA GN GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

122 Ep: pct application non-entry in european phase
DPE2 Request for preliminary examination filed before expiration of 19th month from priority date (pct application filed from 20040101)