GB2303596A - Gas turbine engine containment barrier - Google Patents
Gas turbine engine containment barrier Download PDFInfo
- Publication number
- GB2303596A GB2303596A GB9514926A GB9514926A GB2303596A GB 2303596 A GB2303596 A GB 2303596A GB 9514926 A GB9514926 A GB 9514926A GB 9514926 A GB9514926 A GB 9514926A GB 2303596 A GB2303596 A GB 2303596A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas turbine
- turbine engine
- containment barrier
- barrier
- pylon
- 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- Withdrawn
Links
- 230000004888 barrier function Effects 0.000 title claims abstract description 32
- 239000000463 material Substances 0.000 claims abstract description 27
- 238000010521 absorption reaction Methods 0.000 claims abstract description 9
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 3
- 239000011521 glass Substances 0.000 claims abstract description 3
- 239000004005 microsphere Substances 0.000 claims abstract description 3
- 239000010959 steel Substances 0.000 claims abstract description 3
- 238000009434 installation Methods 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims 1
- 229910000851 Alloy steel Inorganic materials 0.000 abstract 1
- 239000011358 absorbing material Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
-
- 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
- B32B15/00—Layered products comprising a layer of metal
- B32B15/16—Layered products comprising a layer of metal next to a particulate layer
-
- 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
- B32B5/16—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 features of a layer formed of particles, e.g. chips, powder or granules
-
- 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
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/18—Titanium
-
- 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
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/30—Iron, e.g. steel
-
- 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
- B32B2605/00—Vehicles
- B32B2605/18—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
- 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
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- Laminated Bodies (AREA)
Abstract
An aircraft engine support pylon 11 carries two gas turbine engines 12 and 13 in side-by-side relationship. The pylon 11 incorporates a containment barrier 17 comprising alternate layers of a deformable metallic sheet material (18) (figure 4) and an energy absorption material (19). In the event of the uncontained failure of one of the engines, the containment barrier provides protection of the other engine. The sheet material (18) may be a steel or titanium alloy, and the energy absorption material may comprise glass microspheres or a honeycomb structure.
Description
GAS TURBINE ENGINE CONTAINMENT BARRIER
This invention relates to the installation of gas turbine engines on aircraft. It is particularly concerned with a containment barrier for the protection of one gas turbine engine from damage resulting from the uncontained failure of a further gas turbine engine engine located adjacent thereto.
It is sometimes convenient to mount two aircraft gas turbine engines adjacent to each other within the aircraft fuselage or wing. Alternatively two engines may be mounted from a common support pylon extending from the underside of the aircraft's wing or from the aircraft's fuselage. When gas turbine engines are mounted these ways, it is highly desirable to ensure that if one of the engines should suffer an uncontained failure of one of its rotary components, the other engine is protected from damage by resultant missiles thrown from the failed engine.
One solution to this problem of providing adequate protection is to position a large, thick metallic containment barrier between the engines. Unfortunately this can give rise to undesirable weight penalties.
It is an object of the present invention to provide a gas turbine engine containment barrier which enjoys reduced weight penalties but which nevertheless still provides effective protection.
According to the present invention, a gas turbine engine containment barrier comprises alternate adjacent layers of a sheet material and an energy absorption material, said metallic sheet material being of sufficient strength to be substantially non-frangible when impacted by a missile originating from a gas turbine engine adjacent thereto following an uncontained failure of said engine and thereby deflect said missile, said energy absorption material being chosen so as to be capable of diffusing and dissipating energy resulting from said impact of said sheet material by said missile.
The present invention will now be described, by way of example, with reference to the accompanying drawings in which:
Fig 1 is a partially sectioned side view of a gas turbine engine installation which includes a containment barrier in accordance with the present invention.
Fig 2 is a view on section plane A-A of Fig 1.
Fig 3 is a side view of the pylon which supports the engine shown in Figs 1 and 2.
Fig 4 is a view on section plane B-B of Fig 3.
Fig 5 is a view similar to that shown in Fig 4 in which part of the structure shown has been damaged by a missile ejected from one of the gas turbine engines shown in Fig 2.
With reference to Figs 1 and 2 the wing 10 of an aircraft (not shown) is provided with a generally downwardly and forwardly extending pylon 11, upon which are mounted two ducted fan gas turbine engines 12 and 13.
The engines 12 and 13 are mounted in side-by-side relationship and are of conventional configuration.
The pylon 11 is provided with two pairs of engine mounting members 14 and 15; one pair 14 being positioned forwardly of the other pair 15 as can be seen in Fig 3.
The mounting members of each pair, 14 and 15 are positioned so that one is each side of the pylon 11.
Consequently each side of the pylon 11 carries a first forward mounting member 14 and a second rearward mounting member 15.
Each engine mounting member 14 and 15 carries an engine support bracket 16; the engine support brackets 16 carried by the engine mounting member 14 being visible in
Fig 2. The engine support brackets 16 in turn support the engines 12 and 13.
The pylon 11 is of cenerally conventional construction. However part of the lower portion of the pylon 11 incorporates a containment barrier generally indicated at 17. The structure of the containment barrier 17, which is an integral part of the pylon 11 can be seen more clearly if reference is made to Fig 4. It consists of alternate layers of deformable metallic sheet material 18 and an energy absorption material 19, all of which are adjacent each other.
The deformable metallic sheet material is of sufficient ductility to be capable of deforming locally as shown in Fig 5 when impacted by a missile originating from one of the engines 12 and 13 following an uncontained failure of that engine. Thus the sheet material could be formed from, for instance, a steel or a titanium alloy.
The energy absorbing material situated adjacent the sheet material 18 is intended to diffuse and dissipate the energy released following the impact of the sheet material 18 by the missile. This ensures that damage inflicted upon the containment barrier 17 by the missile is localised, thereby in turn minimising the likelihood of damage to the pylon 11. It will be appreciated however that in order to achieve this end, it is not essential that the sheet material is deformable. It is essential, however, that the sheet material is substantially non-frangible in order that it deflects the missile effectively and so that the energy absorption material is capable of diffusing and dissipating the energy which results from the missile impact.Any suitable energy absorbing material could be employed for instance flash (which comprises small hollow glass microspheres) or a honeycomb material of appropriate density
In the embodiment of the present invention described above, four pieces of the sheet material 18 are sed in conjunction with three layers of the energy absorbing material 19. It will be appreciated that this is by way of example only and that these numbers may be increased or reduced as appropriate in specific applications.
The containment barrier 17 therefore provides effective protection for one of the engines 12 and 13 in the event that the other engine suffers an uncontained failure of one of its rotary components. Any missile ejected from the failed engine impacts the containment barrier 17 and is then deflected away from the adjacent engine. The adjacent engine is consequently able to continue to operate effectively. The containment barrier 17 also serves to protect components within the remainder of the pylon 11 such as fuel pipes and electrical equipment from damage by the missile.
Although in the embodiment of the present invention described above, the containment barrier 17 is an integral part of the pylon 11 and effectively constitutes a structural part of the pylon 11, it will be appreciated that tis is not in fact an essential feature of the present invention. The containment barrier 17 could in fact be structurally independent of the pylon 11.
Moreover, the containment barrier 17 could be used in conjunction with one or more engines which are not mounted on a pylon but are instead mounted within an aircraft inside its fuselage or wing. In such applications, the containment barrier 17 would serve to protect an adjacent engine from an engine suffering from an uncontained failure or alternatively protect part of the aircraft's structure. Alternatively in the case of engines which are mounted externally of the aircraft fuselage on pylons attached to the fuselage, the containment barrier 17 could be located within the fuselage adjacent the pylons.
Claims (9)
1. A gas turbine engine containment barrier comprising alternate adjacent layers of a sheet material and an energy absorption material, said sheet material being of sufficient strength to be substantially non-frangible when impacted by a missile originating from a gas turbine adjacent thereto following an uncontained failure of said engine to thereby deflect said missile, said energy absorption material being chcsen so as to be capable of diffusing and dissipating energy resulting from said impact of said sheet material by said missile.
2. A gas turbine engine containment barrier as claimed in claim 1 wherein said sheet is formed from a deformable metallic material which is sufficiently ductile to deform locally when impacted by said missile.
3. A gas turbine engine containment barrier as claimed in claim 1 or claim 2 wherein said barrier is associated with a pylon for supporting two gas turbine engines in side-by-side relationship.
4. A gas turbine engine containment barrier as claimed in claim 3 wherein said barrier is an integral part of said pylon.
5. A gas turbine engine containment barrier as claimed in claim 4 wherein said barrier is a structural part of said pylon.
6. A gas turbine engine containment barrier as claied in any preceding claim wherein said sheet material is a steel or a titanium alloy.
7. A gas turbine engine containment barrier as clawed in any preceding claim wherein said energy absorption material is of honeycomb configuration or is formed from hollow glass microspheres.
8. A gas turbine engine containment barrier substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
9. A gas turbine engine installation comprising at least one gas turbine engine having a containment barrier as claimed in any one preceding claim adjacent thereto.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9514926A GB2303596A (en) | 1995-07-20 | 1995-07-20 | Gas turbine engine containment barrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9514926A GB2303596A (en) | 1995-07-20 | 1995-07-20 | Gas turbine engine containment barrier |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9514926D0 GB9514926D0 (en) | 1995-09-27 |
| GB2303596A true GB2303596A (en) | 1997-02-26 |
Family
ID=10778017
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9514926A Withdrawn GB2303596A (en) | 1995-07-20 | 1995-07-20 | Gas turbine engine containment barrier |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2303596A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3061149A1 (en) * | 2016-12-27 | 2018-06-29 | Airbus Operations | PRIMARY STRUCTURE OF A MAT FOR AN AIRCRAFT PROPELLER COMPRISING A PYRAMIDAL PART WITH CONVERGENT AMOUNTS |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2095749A (en) * | 1981-03-25 | 1982-10-06 | Rolls Royce | Gas turbine engine having improved resistance for foreign object ingestion damage |
| GB2246818A (en) * | 1990-06-18 | 1992-02-12 | Gen Electric | Rotor blade / projectile shield for use in a gas turbine engine. |
| GB2265184A (en) * | 1992-03-10 | 1993-09-22 | Rolls Royce Plc | Gas turbine engine support structure. |
| GB2265418A (en) * | 1992-03-26 | 1993-09-29 | Rolls Royce Plc | Gas turbine engine casing blade containment. |
-
1995
- 1995-07-20 GB GB9514926A patent/GB2303596A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2095749A (en) * | 1981-03-25 | 1982-10-06 | Rolls Royce | Gas turbine engine having improved resistance for foreign object ingestion damage |
| GB2246818A (en) * | 1990-06-18 | 1992-02-12 | Gen Electric | Rotor blade / projectile shield for use in a gas turbine engine. |
| GB2265184A (en) * | 1992-03-10 | 1993-09-22 | Rolls Royce Plc | Gas turbine engine support structure. |
| GB2265418A (en) * | 1992-03-26 | 1993-09-29 | Rolls Royce Plc | Gas turbine engine casing blade containment. |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3061149A1 (en) * | 2016-12-27 | 2018-06-29 | Airbus Operations | PRIMARY STRUCTURE OF A MAT FOR AN AIRCRAFT PROPELLER COMPRISING A PYRAMIDAL PART WITH CONVERGENT AMOUNTS |
Also Published As
| Publication number | Publication date |
|---|---|
| GB9514926D0 (en) | 1995-09-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |