GB2120972A - Composite structure - Google Patents

Composite structure Download PDF

Info

Publication number
GB2120972A
GB2120972A GB08215398A GB8215398A GB2120972A GB 2120972 A GB2120972 A GB 2120972A GB 08215398 A GB08215398 A GB 08215398A GB 8215398 A GB8215398 A GB 8215398A GB 2120972 A GB2120972 A GB 2120972A
Authority
GB
United Kingdom
Prior art keywords
filaments
composite structure
sealing means
backing member
fibres
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.)
Withdrawn
Application number
GB08215398A
Inventor
John William Johnson
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB08215398A priority Critical patent/GB2120972A/en
Publication of GB2120972A publication Critical patent/GB2120972A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/026—Knitted fabric
    • 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
    • F02C7/24—Heat or noise insulation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/103—Metal fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Textile Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Woven Fabrics (AREA)
  • Thermal Insulation (AREA)
  • Exhaust Silencers (AREA)

Abstract

A composite structure for use as a heat insulator comprises a backing member having a plurality of filaments extending from one face thereof to the ends of filaments remote from the backing member being enlarged to form a sealing surface or alternatively the ends serving to carry a layer of refractory material. <IMAGE>

Description

SPECIFICATION Composite structure This invention relates to composite structures and more particularly to such structures suitable for use as an insulating material in a gas turbine engine.
It has been well known in the past to use insulating structures in gas turbine engines to insulate engine components from the hot exhaust gas stream. Such structures have usually comprised refractory materials or honeycomb materials. These structures have usually suffered the disadvantages of either being relatively heavy or alternatively difficult to secure within the engine.
An object of the present invention is to provide an insulating material which substantially overcomes the aforementioned problems.
According to the present invention a composite structure comprises a plenar backing member having a plurality of filaments extending from one face thereof, which filaments include sealing means on their respective ends remote from the backing member which sealing means provide a face substantially parallel to the backing member.
Preferably the filaments comprise fibres or tufts of fibres which are secured to the backing member by bonding or alternatively the filaments may be woven or knitted into the backing member and form an integral part thereof.
The sealing means provided upon the filaments may consist of a refractory sheet which is bonded to -the ends of the filaments.
Alternatively the sealing means provided upon the filaments may comprise upset portions which are formed upon the ends of the filaments which upset portions lie in close proximity to each other.
Furthermore the upset portions may be formed by melting the individual ends of the filaments or alternatively by deposition of a material onto the ends thereof.
Alternatively the sealing means provided upon the filaments may comprise intumescent paint provided upon the fibre end which expands under the influence of temperature to provide the sealing means.
Preferably the filaments comprise single filaments or a plurality of filaments of carbon, glass, refractory or metallic fibres.
For better understanding of the invention several embodiments thereof will be more particularly described by way of example only and with reference to the accompanying drawings in which: Figure 1 shows a pictorial side view of a gas turbine engine having a broken away casing portion disclosing a diagrammatic embodiment of the present invention.
Figure 2 shows an enlarged cross-sectional view in greater detail of the embodiment shown diagram- matically at Figure 1.
Figure 3 shows a cross-sectional view of a further embodiment of the present invention.
Referring to the drawings a gas turbine engine shown generally at 10 comprises in flow series compressor section 12, combustion equipment 13, turbine section 14, the engine terminating in an exhaust nozzle 15. The exhaust nozzle casing portlon is broken away at 17 to disclose a diagrammatic embodiment of the present invention.
Figure 2 of the drawings shows an enlarged cross-sectional view In greater detail of the embody ment shown diagrammatically at Figure 1. This consists of a portion of the engine exhaust casing 15 to which is secured a backing member 16 which serves to carry a plurality of filaments 17. The filaments 17 may consist af single filaments or bundles of glass, carbon, metallic or refractory fibres which may be secured to the backing member by any suitable means such as for example bonding or in the case of a metallic fibre, a metallurgical bond or weld. Alternatively the fibres and backing member may be a single integral knitted or woven structure manufactured by method conventionally used in the manufacture of carpets.
The sealing means 18 located on the filament ends remote from the backing member 16 may comprise upset fibre portions which are produced by locally heating the ends of the fibres to melt and thicken them such that they fuse completely together or alternatively leave small gaps between the individual upset portions to allow for the passage of cooling airtherethrough.
Alternatively the upset portions may be formed by coating the ends of the filaments remote from the backing sheet 15 with an intuinescent paint. The structure is then heated to expand the paint and so produce the necessary sealing means.
The use of intumescent paint is well known in the gas turbine engine art, such material usually being used for protective gas turbine parts in excessive temperatures.
The term "intumescent paint" is applied to heat protective paint which when exposed to a flame or high temperature, bubbles and swells forming a relatively thick cellular flame resistant protective layer. This layer prevents the substrate to which the paint is adherent from being charred or burnt by flame or high temperature.
Many proprietory brands of such paint exist however a typical paint may consist of Expoxy resin ester 700 gms, Melamine-formaldehyde resin 175 gms, Dicandiamide 420 gms, Polyammonium phosphate 700 gms, Melamine 150 gms, Pentaerythritoal 300 gms, Titanium dioxide 100 gms, Xylene 400 gms and n butonal 100 gms.
Alternatively the ends of the fibre 17 may be upset by vapour deposition at or adjacent their ends to provide the necessary sealing means which may or may not be provided with air spaces between the filament depending upon the operating condition for which the material is intended.
Alternatively the sealing means 18 as shown in Figure 3 may simply consist of a layer of suitable refractory cloth such as for example woven asbestos cloth which is bonded to the filament ends with a suitable cement.
It will be appreciated frorn the forgoing that the described embodiments provide a composite insulating material suitable for use in locations such as for example gas turbine engines where a lightweight highly efficient heat insulator is required. It will be appreciated that its effectiveness may be further increased by blowing a supply of cooling air through the space defined by the backing layer 16 and the sealing means 18. The cooling air may either simply impinge upon the sealing means 18 or pass through apertures provided within it to improve its effectiveness.

Claims (9)

1. A composite structure comprising a backing member having a plurality of filaments extending from one face thereof, which filaments include sealing means on their respective ends remote from the backing member, which sealing means provide a face substantially parallel to the backing member.
2. A composite structure as claimed in claim 1 in which the filaments comprise fibres or tufts of fibres which are secured to the backing member by bonding or alternatively the filaments may be woven or knitted into the backing member to form an integral part thereof.
3. A composite structure as claimed in claim 1 and 2 in which the sealing means provided upon the ends of the filaments consist of a refractory sheet which is bonded to the ends of the filaments.
4. A composite structure as claimed in claim 1 and 2 in which the sealing means provided upon the ends of the filaments comprise upset portions which are formed upon the ends of the filaments, which upset portions lie in close proximity to each other.
5. A composite structure as claimed in claim 4 in which the upset portions may be formed by melting the individual ends of the filaments, or alternatively by vapour deposition of a material upon their ends,
6. A composite structure as claimed in claim 4 in which the upset portions comprise intumescent paint provided upon the fibre ends which expands under the influence of temperature to provide the sealing means.
7. A composite structure as claimed in any preceding claim in which the filaments comprise single filaments or a plurality of filaments of carbon, glass, refractory, or metallic fibres.
8. A composite structure for use as a heat insulating material in a gas turbine engine.
9. A composite structure as claimed in any preceding claim substantially as hereinbefore described by way of example only and as illustrated in the accompanying drawings.
GB08215398A 1982-05-26 1982-05-26 Composite structure Withdrawn GB2120972A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB08215398A GB2120972A (en) 1982-05-26 1982-05-26 Composite structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08215398A GB2120972A (en) 1982-05-26 1982-05-26 Composite structure

Publications (1)

Publication Number Publication Date
GB2120972A true GB2120972A (en) 1983-12-14

Family

ID=10530643

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08215398A Withdrawn GB2120972A (en) 1982-05-26 1982-05-26 Composite structure

Country Status (1)

Country Link
GB (1) GB2120972A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2390569A (en) * 2002-07-10 2004-01-14 Alstom Ceramic materials for thermal insulation
US7011724B2 (en) * 2001-11-15 2006-03-14 Interface, Inc. Textile products having flame retardant properties and methods of manufacture

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB721338A (en) * 1951-10-22 1955-01-05 Velcro Sa Soulie Improvements in or relating to a method and a device for producing a velvet type fabric
GB1393091A (en) * 1971-06-09 1975-05-07 Ici Ltd Packaging
GB1394824A (en) * 1971-06-09 1975-05-21 Ici Ltd Production of laminated products
GB1403322A (en) * 1972-02-17 1975-08-28 Rockwool Ab Method of manufacturing a block of spun mineralwool fibres having two substantially parallel main surfaces and in which the fibres are arranged in layers substantially normal to the main surfaces and an apparatus for carrying out the method
GB1528354A (en) * 1975-11-10 1978-10-11 Ici Ltd Laminated fibrous structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB721338A (en) * 1951-10-22 1955-01-05 Velcro Sa Soulie Improvements in or relating to a method and a device for producing a velvet type fabric
GB1393091A (en) * 1971-06-09 1975-05-07 Ici Ltd Packaging
GB1394824A (en) * 1971-06-09 1975-05-21 Ici Ltd Production of laminated products
GB1403322A (en) * 1972-02-17 1975-08-28 Rockwool Ab Method of manufacturing a block of spun mineralwool fibres having two substantially parallel main surfaces and in which the fibres are arranged in layers substantially normal to the main surfaces and an apparatus for carrying out the method
GB1528354A (en) * 1975-11-10 1978-10-11 Ici Ltd Laminated fibrous structure

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7011724B2 (en) * 2001-11-15 2006-03-14 Interface, Inc. Textile products having flame retardant properties and methods of manufacture
US7736716B2 (en) 2001-11-15 2010-06-15 Interface, Inc. Textile products having flame retardant properties and methods of manufacture
GB2390569A (en) * 2002-07-10 2004-01-14 Alstom Ceramic materials for thermal insulation

Similar Documents

Publication Publication Date Title
CA2580128C (en) Flexible heat shields and method
US4838031A (en) Internally cooled combustion chamber liner
JP4172913B2 (en) Combustor wall segment and combustor
EP0107727B1 (en) Heat insulating blanket
US4594053A (en) Housing for a fluid flow or jet engine
US5236151A (en) Thermal barrier structure
US5320909A (en) Ceramic thermal barrier coating for rapid thermal cycling applications
US2514170A (en) Insulating material
EP0150656B1 (en) Coated high temperature combustor liner
US5605046A (en) Cooled liner apparatus
US5305726A (en) Ceramic composite coating material
US6047539A (en) Method of protecting gas turbine combustor components against water erosion and hot corrosion
CA2892096C (en) Combustor heat shield
US20060059918A1 (en) Adjusting airflow in turbine component by depositing overlay metallic coating
EP1041344B1 (en) Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein
JP4733852B2 (en) Method and apparatus for increasing heat transfer from a combustor
US3880575A (en) Ceramic combustion liner
AU623954B2 (en) Method of attaching ceramic fiber arrays to metallic substrates
US5622474A (en) Blade tip seal insert
GB2120972A (en) Composite structure
GB2120580A (en) Intumescent paint layers
RU2178530C2 (en) Gas-turbine plant with combustion chamber housing lined with ceramic stones
US3880574A (en) Ceramic combustion liner
KR900007117B1 (en) Appparatus for heating caddless or the like
US5202163A (en) Surface coating for protecting a component against titanium fire and method for making the surface coating

Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)