GB2365925A - Gas turbine engine blade containment with corrugated sheet material - Google Patents

Gas turbine engine blade containment with corrugated sheet material Download PDF

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Publication number
GB2365925A
GB2365925A GB0019664A GB0019664A GB2365925A GB 2365925 A GB2365925 A GB 2365925A GB 0019664 A GB0019664 A GB 0019664A GB 0019664 A GB0019664 A GB 0019664A GB 2365925 A GB2365925 A GB 2365925A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
corrugations
blade containment
containment assembly
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
Application number
GB0019664A
Other versions
GB2365925B (en
GB0019664D0 (en
Inventor
David Geary
Ian Graham Martindale
Julian Mark Reed
Sivasubramaniam K Sathianathan
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 GB0019664A priority Critical patent/GB2365925B/en
Publication of GB0019664D0 publication Critical patent/GB0019664D0/en
Priority to GBGB0116988.7A priority patent/GB0116988D0/en
Priority to US09/924,104 priority patent/US6575694B1/en
Publication of GB2365925A publication Critical patent/GB2365925A/en
Application granted granted Critical
Publication of GB2365925B publication Critical patent/GB2365925B/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An arrangement for containment of detached portions of fan, compressor or turbine blades in a gas turbine engine, comprises at least one corrugated sheet metal ring 54,56,58,60. The corrugations extend with axial and/or circumferential components. One embodiment has concentric rings with corrugations arranged at opposite angles a , a 2, a 3, a 4. Another embodiment (fig 12-14) has corrugations of concentric rings extending purely circumferentially or axially. The rings may surround a generally annular or frustoconical thin metallic inner casing 52, be joined to the casing and flanges 40 at their axial ends, have apertures 63 for acoustic attenuation, foam filling or be surrounded by strong fibrous material 64. The flange 40 may have a fence or hook (45, fig 8) to prevent forward movement of the blade, or a purely circumferential corrugation (59, fig 10) upstream of the rings. Suitable materials for the sheets are disclosed, including steel.

Description

<Desc/Clms Page number 1> A GAS TURBINE ENGINE BLADE CONTAINMENT ASSEMBLY The present invention relates to gas turbine engine casings, particularly gas turbine engine fan casings and turbine casings, more particularly to an improved blade containment assembly for use within or forming a part of the gas turbine engine casing.
Turbofan gas turbine engines for powering aircraft conventionally comprise a core engine, which drives a fan. The fan comprises a number of radially extending fan blades mounted on a fan rotor enclosed by a generally cylindrical, or frustoconical, fan casing. The core engine comprises one or more turbines, each one of which comprises a number of radially extending turbine blades enclosed by a cylindrical, or frustoconical, casing.
There is a remote possibility with such engines that part, or a11, of a fan blade, or a turbine blade, could become detached from the remainder of the fan or turbine. In the case of a fan blade becoming detached this may occur as the result of, for example, the turbofan gas turbine engine ingesting a bird or other foreign object.
The use of containment rings for turbofan gas turbine engine casings is well known. It is known to provide generally cylindrical, or frustoconical, relatively thick metallic containment casings. It is known to provide generally cylindrical, or frustoconical, locally thickened, isogrid, metallic containment casings. It is known to provide strong fibrous material wound around relatively thin metallic casings or around the above mentioned containment casings. In the event that a blade becomes detached it passes through the casing and is contained by the fibrous material.
However, the relatively thick containment casings are relatively heavy, the relatively thin casings enclosed by the fibrous material are lighter but are more expensive to manufacture. The relatively thick casings with fibrous material are both heavier and more expensive to manufacture.
<Desc/Clms Page number 2>
Accordingly the present invention seeks to provide a novel gas turbine engine casing which overcomes the above mentioned problems.
Accordingly the present invention a gas turbine engine blade containment assembly comprising a generally cylindrical, or frustoconical, casing, the casing being arranged in operation to surround a rotor carrying a plurality of radially extending rotor blades, at least corrugated sheet metal ring surrounding the casing, wherein the corrugations of the at least one corrugated sheet metal ring extend with axial and/or circumferential components.
Preferably the casing is a fan casing and the rotor blades are fan blades.
Alternatively the casing may be a turbine casing and the rotor blades are turbine blades.
Preferably the corrugations are equi-spaced.
The corrugations in the at least one corrugated sheet metal ring may extend with purely axial components. The corrugations in the at least one corrugated sheet metal ring may extend with purely circumferential components. Preferably the corrugations in the at least one corrugated sheet metal ring extend with both axial and circumferential components.
The casing may comprise a single metal sheet wound into a ring.
Preferably the casing comprises a plurality of metal sheets, each of which is wound into a ring and each one of which is corrugated.
Preferably the corrugations in different metal sheets are arranged to extend at different angles.
The corrugations in a first metal sheet may be arranged to extend with purely axial components and the corrugations in a second metal sheet are arranged to extend with purely circumferential components.
The corrugations in a first metal sheet may be arranged to extend with purely axial components and the corrugations
<Desc/Clms Page number 3>
in a second metal sheet are arranged to extend with axial and circumferential components.
The corrugations in a first metal sheet may be arranged to extend with purely circumferential components and the corrugations in a second metal sheet are arranged to extend with axial and circumferential components.
Preferably the corrugations in a first metal sheet are arranged to extend with axial and circumferential components and the corrugations in a second metal sheet are arranged to extend with axial and circumferential components.
The at least one metal sheet may be provided with apertures therethrough to attenuate noise.
The plurality of metal sheets define spaces therebetween, the spaces may be filled with an energy absorbing material to increase the blade containment capability of the casing.
Preferably the at least one metal sheet is formed from titanium, an alloy of titanium, aluminium or steel.
The present invention will be more fully described by way of example with reference to the accompanying drawings in which:- Figure 1 is a partially cut away view of a gas turbine engine having a fan blade containment assembly according to the present invention.
Figure 2 is an enlarged view of the fan blade containment assembly shown in figure 1.
Figure 3 is a further enlarged view of the fan blade containment assembly shown in figure 2.
Figure 4 is a cross-sectional view in the direction of arrows A-A in figure 3.
Figure 5 is a view in the direction of arrow B in figure 3.
Figure 6 is a cut away view in the direction of arrow C in figure 3.
<Desc/Clms Page number 4>
Figure 7 is a cut away perspective view of the fan blade containment assembly shown in figure 3, showing two of the corrugated metal rings.
Figure 8 is a cross-sectional view of an alternative attachment of the fan blade containment assembly to the fan casing.
Figure 9 is a cross-sectional view of a further attachment of the fan blade containment assembly to the fan casing.
Figure 10 is a cut away perspective view of a single sheet fan blade containment assembly according to the present invention.
Figure 11 is an alternative view in the direction of arrow B in figure 3.
Figure 12 is an enlarged view of an alternative fan blade containment assembly shown in figure 1.
Figure 13 is a further enlarged view of the fan blade containment assembly shown in figure 12.
Figure 14 is a view in the direction of arrow D in figure 13.
A turbofan gas turbine engine 10, as shown in figure 1, comprises in flow series an intake 12, a fan section 14, a compressor section 16, a combustor section 18, a turbine section 20 and an exhaust 22. The turbine section 20 comprises one or more turbines arranged to drive one or more compressors in the compressor section 16 via shafts. The turbine section 20 also comprises a turbine to drive the fan section 14 via a shaft. The fan section 14 comprises a fan duct 24 defined partially by a fan casing 26. The fan duct 24 has an outlet 28 at its axially downstream end. The fan casing 26 is secured to the core engine casing 36 by a plurality of radially extending fan outlet guide vanes 30. The fan casing 26 surrounds a fan rotor 32 which carries a plurality of circumferentially spaced radially extending fan blades 34. The fan casing 26 also comprises a fan blade
<Desc/Clms Page number 5>
containment assembly 38, which is arranged substantially in the plane of the fan blades 34.
The fan casing 26 and fan blade containment assembly 38 are shown more clearly in figures 2 to 7. The fan blade containment assembly 38 comprises an upstream flange 40 by which the fan blade containment assembly 38 is connected to a flange 46 on an intake assembly 44 of the fan casing 26 and the fan blade containment assembly 38 has a downstream flange 42 by which the fan blade containment assembly 38 is connected to a flange 50 on a rear portion 48 of the fan casing 26.
The fan blade containment assembly 38, as shown more clearly in figures 3 and 4, comprises a relatively thin metallic cylindrical, or frustoconical, casing 52 and a plurality of relatively thin corrugated metallic sheets 54, 56, 58 and 60. The thin corrugated metallic sheet 54 is wound into a ring around the casing 52 and the circumferential ends of the thin corrugated metallic sheet 54 are joined together by suitable means, for example welding, brazing, nuts and bolts or other mechanical fasteners. Similarly the thin corrugated metallic sheets 56, 58 and 60 in turn are wound around the casing 52 and the respective ends of the thin corrugated metallic sheets are joined together to form substantially concentric rings. The axial ends of the thin corrugated metallic sheets 54, 56, 58 and 60 are joined to each other and the casing 52 by welding or other suitable means or retained by band clamps. The axial ends of the casing 52 are provided with the flanges 40 and 42. The thin corrugated metallic sheets 54, 56, 58 and 60 are arranged to abut each other at axially and circumferentially spaced locations where the corrugations 62 contact. The thin corrugated metallic sheets 54, 56, 58 and 60 are spot welded, or seam welded, together at the spaced locations where the corrugations 62 contact to improve the rigidity, or integrity, of the fan blade containment assembly 38. The corrugations 62 of the thin corrugated metallic
<Desc/Clms Page number 6>
sheets 54, 56, 58 and 60 are shown more clearly in figures 4, 5, 6 and 7.
In some circumstances the welds between the corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 may not be required.
The corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 are arranged to extend with both axial and circumferential components. Additionally the corrugations 62 on the adjacent thin corrugated metallic sheets 54, 56, 58 and 60 are arranged at different angles. For example the corrugations 62 on metallic sheet 54 are arranged at an angle oc to the axis X of the gas turbine engine 10. The corrugations 62 on the metallic sheet 56 are arranged at angle oc2 to the axis X of the gas turbine engine 10. The corrugations 62 on metallic sheet 58 are arranged at an angle oc3 to the axis X of the gas turbine engine 10 and the corrugations 62 on the metallic sheet 60 are arranged at angle oc4 to the axis X of the gas turbine engine 10. The angles oc, oc2, oc3 and oc4 are the same, 45 in this example, but angles oc and oc3 are in the opposite direction to angles oc2 and oc4. It would of course be possible to use any suitable combinations of angles oc, oc2, oc3 and oc4.
The thin casing 52 and the thin corrugated metallic sheets 54, 56, 58 and 60 are provided with apertures 63 to provide acoustic attenuation of sounds generated in the gas turbine engine 10. The corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 define spaces 61 therebetween and the spaces 61 may be filled with an energy absorbing material, for example foam, to further increase the energy absorbing capability of the fan blade containment assembly 38.
It may be desirable in some circumstances to provide a number of continuous layers of a strong fibrous material 64 wound around the thin corrugated metallic sheets 54, 56, 58 and 60 to further increase the energy absorbing capability of
<Desc/Clms Page number 7>
the fan blade containment assembly 38. The strong fibrous material may for example be woven aromatic polyamide fibres known as KEVLAR (KEVLAR is a registered trademark of Dupont Ltd). There may also be a number of layers of discrete pieces of flexible material woven from KEVLAR between the thin corrugated metallic sheets 54, 56, 58 and 60 and the continuous layers of fibrous material 64.
Figure 8 shows an attachment of the fan blade containment assembly 38 to the flanges 40 and 42. The axial ends of the thin metallic sheets 54, 56, 58 and 60 are mechanically fastened by nuts and bolts 47 to the flanges 40 and 42. However, welding, brazing or other suitable fastening may be used. It is to be noted that a fence, or hook, 45 is provided on the flange 40 to prevent forward movement of the tip of the fan blades 34 in the event of a fan blade off situation.
Figure 9 shows a corrugation 59 extending with a purely circumferential component at the upstream end of the fan blade containment assembly 38 to attach the fan blade containment assembly 38 to the flange 40.
Figure 10 shows a single thin corrugated metallic sheet wound into a ring to form the fan blade containment assembly 38. The corrugations 62 extend with both axial and circumferential components. It may be possible to arrange the corrugations 62 to extend with purely an axial component or purely a circumferential component.
Figure 11 shows an alternative view of the fan blade containment assembly 38 in which the thin corrugated metallic sheet 60 has the corrugations extending with a pure axial component. But one or more of the thin corrugated metallic sheets 54, 56 and 58 may have corrugations 62 extending with both circumferential and axial components, with purely circumferential components or with purely axial components.
Figures 12, 13 and 14 show an alternative fan blade containment assembly 38B which comprises a relatively thin metallic cylindrical, or frustoconical, casing 52 and a
<Desc/Clms Page number 8>
plurality of, four, relatively thin corrugated metallic sheets 54, 56, 58 and 60. The thin corrugated metallic sheet 54 is wound into a ring around the casing 52 and the circumferential ends of the thin corrugated metallic sheet 54 are joined together by suitable means, for example welding, brazing, nuts and bolts or other mechanical fasteners. Similarly the thin corrugated metallic sheets 56, 58 and 60 in turn are wound around the casing 52 and the respective circumferential ends of the thin corrugated metallic sheets are joined together to form substantially concentric rings. The axial ends of the thin corrugated metallic sheets 54, 56, 58 and 60 are joined to each other and the casing 52 by welding or other suitable means or retained by band clamps. The axial ends of the casing 52 are provided with the flanges 40 and 42. The thin corrugated metallic sheets 54, 56, 58 and 60 are arranged to abut each other at axially and circumf erentially spaced locations where the corrugations 62 contact. The thin corrugated metallic sheets 54, 56, 58 and 60 are spot welded, or seam welded, together at the spaced locations where the corrugations 62 contact to improve the rigidity, or integrity, of the fan blade containment assembly 38. The corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 are shown more clearly in figures 13 and 14.
The corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 are arranged to extend with pure circumferential components.
The thin casing 52 and the thin corrugated metallic sheets 54, 56, 58 and 60 are provided with apertures 63 to provide acoustic attenuation of sounds generated in the gas turbine engine 10. The corrugations 62 of the thin corrugated metallic sheets 54, 56, 58 and 60 define spaces 61 therebetween and the spaces 61 may be filled with an energy absorbing material, for example foam, to further increase the energy absorbing capability of the fan blade containment assembly 38B.
<Desc/Clms Page number 9>
It may be desirable in some circumstances to provide a number of continuous layers of a strong fibrous material 64 wound around the thin corrugated metallic sheets 54, 56, 58 and 60 to further increase the energy absorbing capability of the fan blade containment assembly 38. The strong fibrous material may for example be woven aromatic polyamide fibres known as KEVLAR (KEVLAR is a registered trademark of Dupont Ltd). There may also be a number of layers of discrete pieces of flexible material woven from KEVLAR between the thin corrugated metallic sheets 54, 56, 58 and 60 and the continuous layers of fibrous material 64.
The thin casing 52 and the thin corrugated metallic sheets 54, 56, 58 and 60 have a thickness of about 1-3mm, preferably 2mm, compared to the conventional thickness of 12mm for a fan blade containment casing. This enables the weight of the fan blade containment assembly to be reduced. Additionally it may allow the use of the fibrous material for fan blade containment to be dispensed with.
In operation of the gas turbine engine 10, in the event that a fan blade 34, or a portion of a fan blade 34, becomes detached it pierces the thin metallic casing 52, before it encounters the thin corrugated metallic sheets 54, 56, 58 and 60. The thin corrugated metallic sheets 54, 56, 58 and 60 are impacted by the fan blade 34, or portion of the fan blade 34, and effectively remove energy from the fan blade 34, or portion of the fan blade 34.
Each of the thin corrugated metallic sheets 54, 56, 58 and 60 has relatively low mass and hence low inertia. This allows the thin corrugated metallic sheets 54, 56, 58 and 60 to move with the detached fan blade 34, or portion of the fan blade 34. This movement spreads the impact energy over a larger area of the fan blade containment assembly 38 enabling the use of a lower mass of material to contain the detached fan blade 34, or portion of the fan blade 34.
The detached fan blade 34, or portion of the fan blade 34, causes the corrugations 62 in the thin corrugated
<Desc/Clms Page number 10>
metallic sheets 54, 56, 58 and 60 to be straightened out and this process absorbs energy from the detached fan blade 34 or portion of the fan blade 34. As the corrugations 62 are straightened out sequentially in the adjacent thin corrugated metallic sheets 54, 56, 58 and 60, the adjacent thin metallic sheets 54, 56, 58 and 60 slide over each other and absorb more energy from the fan blade 34 by friction between the adjacent thin corrugated metallic sheets 54, 56, 58 and 60. As the corrugations 62 are straightened out the welds between the corrugations 62 on adjacent thin corrugated metallic sheets 54, 56, 58 and 60 are broken, this also absorbs more energy. As each thin corrugated metallic sheet 54, 56, 58 and 60 is straightens over the impact region it stiffens locally and transfers load to material further from the impact region, this increases the proportion of the fan blade containment assembly 38 contributing to energy absorption.
The corrugations lead to a low-density structure with a greater stiffness to weight ratio than a solid casing of the same material.
The orientation of the corrugations relative to the axis of the gas turbine engine allows the elongation axially and circumferentially to be adjusted to an optimum for fan blade containment.
The use of a plurality of thin corrugated metallic sheets with the corrugations arranged at different angles to the axis of the gas turbine engine to increase the torsional rigidity of the fan blade containment assembly and/or to ensure consistent spacing between the thin corrugated metallic sheets. The use of a plurality of thin corrugated metallic sheets provides high integrity through the alternative load paths and hence damage tolerance.
The thin corrugated metallic sheets are easy to produce by passing thin metallic sheets through shaped rollers to form the corrugations.
The thin metallic sheet may be lower cost material because defects are easier to detect in then metallic sheets
<Desc/Clms Page number 11>
and/or the defects have less significance due to the multiple rings of the thin corrugated metallic sheet (s).
The thin corrugated metallic sheets may be manufactured from titanium, titanium alloy, aluminium, aluminium alloy, nickel, nickel alloy, titanium aluminide, nickel aluminide or steel.
The spacing between the corrugations and the radial height of the corrugations in the thin corrugated metallic sheets is selected to provide optimum energy absorption.
The invention has been described with reference to a fan blade containment assembly, however it is equally applicable to a compressor blade containment assembly and a turbine blade containment assembly.
Although the description has referred to the use of corrugated metallic sheets arranged concentrically around a thin metallic casing in some circumstances the thin metallic casing may not be required.
<Desc/Clms Page number 12>

Claims (20)

  1. claims:- 1. A gas turbine engine blade containment assembly comprising a generally cylindrical, or frustoconical, casing, the casing being arranged in operation to surround a rotor carrying a plurality of radially extending rotor blades, at least corrugated sheet metal ring surrounding the casing, wherein the corrugations of the at least one corrugated sheet metal ring extend with axial and/or circumferential components.
  2. 2. A gas turbine engine blade containment assembly as claimed in claim 1 wherein the casing is a fan casing and the rotor blades are fan blades.
  3. 3. A gas turbine engine blade containment assembly as claimed in claim 1 wherein the casing is a turbine casing and the rotor blades are turbine blades.
  4. 4. A gas turbine engine blade containment assembly as claimed in claim 1, claim 2 or claim 3 wherein the corrugations are equi-spaced.
  5. 5. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 4 wherein the corrugations in the at least one corrugated sheet metal ring extend with purely axial components.
  6. 6. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 4 wherein the corrugations in the at least one corrugated sheet metal ring extend with purely circumferential components.
  7. 7. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 4 wherein the corrugations in the at least one corrugated sheet metal ring extend with both axial and circumferential components.
  8. 8. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 7 wherein the casing comprises a single metal sheet wound into a ring.
  9. 9. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 7 wherein the casing comprises
    <Desc/Clms Page number 13>
    a plurality of metal sheets, each of which is wound into a ring and each one of which is corrugated.
  10. 10. A gas turbine engine blade containment assembly as claimed in claim 9 wherein the corrugations in different metal sheets are arranged to extend at different angles.
  11. 11. A gas turbine engine blade containment assembly as claimed in claim 10 wherein the corrugations in a first metal sheet are arranged to extend with purely axial components and the corrugations in a second metal sheet are arranged to extend with purely circumferential components.
  12. 12. A gas turbine engine blade containment assembly as claimed in claim 10 wherein the corrugations in a first metal sheet are arranged to extend with purely axial components and the corrugations in a second metal sheet are arranged to extend with axial and circumferential components.
  13. 13. A gas turbine engine blade containment assembly as claimed in claim 10 wherein the corrugations in a first metal sheet are arranged to extend with purely circumferential components and the corrugations in a second metal sheet are arranged to extend with axial and circumferential components.
  14. 14. A gas turbine engine blade containment assembly as claimed in claim 10 wherein the corrugations in a first metal sheet are arranged to extend with axial and circumferential components and the corrugations in a second metal sheet are arranged to extend with axial and circumferential components.
  15. 15. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 14 wherein the at least one metal sheet is provided with apertures therethrough to attenuate noise.
  16. 16. A gas turbine engine blade containment assembly as claimed in any of claims 9 to 14 wherein the plurality of metal sheets define spaces therebetween, the spaces are filled with a energy absorbing material to increase the blade containment capability of the casing.
  17. 17. A gas turbine engine blade containment assembly as claimed in any of claims 1 to 16 wherein the at least one
    <Desc/Clms Page number 14>
    metal sheet is formed from titanium, an alloy of titanium, aluminium or steel.
  18. 18. A gas turbine engine blade containment assembly substantially as hereinbefore described with reference to and as shown in figures 1 to 7 of the accompanying drawings.
  19. 19. A gas turbine engine blade containment assembly substantially as hereinbefore described with reference to and as shown in figures 12 to 14 of the accompanying drawings.
  20. 20. A gas turbine engine comprising a blade containment assembly as claimed in any of claims 1 to 19.
GB0019664A 2000-08-11 2000-08-11 A gas turbine engine blade containment assembly Expired - Fee Related GB2365925B (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB0019664A GB2365925B (en) 2000-08-11 2000-08-11 A gas turbine engine blade containment assembly
GBGB0116988.7A GB0116988D0 (en) 2000-08-11 2001-07-12 A gas turbine engine blade containment assembly
US09/924,104 US6575694B1 (en) 2000-08-11 2001-08-08 Gas turbine engine blade containment assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0019664A GB2365925B (en) 2000-08-11 2000-08-11 A gas turbine engine blade containment assembly

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Publication Number Publication Date
GB0019664D0 GB0019664D0 (en) 2000-09-27
GB2365925A true GB2365925A (en) 2002-02-27
GB2365925B GB2365925B (en) 2005-02-23

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2434837A (en) * 2006-02-07 2007-08-08 Rolls Royce Plc Gas turbine engine containment system
EP2096269A3 (en) * 2008-02-27 2013-03-20 Rolls-Royce plc Fan track liner assembly for a gas turbine engine
EP3311934A1 (en) * 2016-10-21 2018-04-25 Rolls-Royce plc Complementary structure
EP3656988A1 (en) * 2018-11-23 2020-05-27 Rolls-Royce plc Fan containment
CN113446123A (en) * 2020-03-26 2021-09-28 和谐工业有限责任公司 Air turbine starter containment system

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US3974313A (en) * 1974-08-22 1976-08-10 The Boeing Company Projectile energy absorbing protective barrier
GB1500135A (en) * 1973-02-23 1978-02-08 Int Harvester Co Seals
GB1533017A (en) * 1975-11-10 1978-11-22 Caterpillar Tractor Co Modular gas turbine engine assembly
US4762462A (en) * 1986-11-26 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Housing for an axial compressor

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US1698514A (en) * 1927-05-20 1929-01-08 Westinghouse Electric & Mfg Co Restraining guard for rotors
US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4618152A (en) * 1983-01-13 1986-10-21 Thomas P. Mahoney Honeycomb seal structure

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Publication number Priority date Publication date Assignee Title
GB1500135A (en) * 1973-02-23 1978-02-08 Int Harvester Co Seals
US3974313A (en) * 1974-08-22 1976-08-10 The Boeing Company Projectile energy absorbing protective barrier
GB1533017A (en) * 1975-11-10 1978-11-22 Caterpillar Tractor Co Modular gas turbine engine assembly
US4762462A (en) * 1986-11-26 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Housing for an axial compressor

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2434837A (en) * 2006-02-07 2007-08-08 Rolls Royce Plc Gas turbine engine containment system
GB2434837B (en) * 2006-02-07 2008-04-09 Rolls Royce Plc A containment system for a gas turbine engine
US7806364B1 (en) 2006-02-07 2010-10-05 Rolls-Royce Plc Containment system for a gas turbine engine
EP2096269A3 (en) * 2008-02-27 2013-03-20 Rolls-Royce plc Fan track liner assembly for a gas turbine engine
EP3311934A1 (en) * 2016-10-21 2018-04-25 Rolls-Royce plc Complementary structure
EP3656988A1 (en) * 2018-11-23 2020-05-27 Rolls-Royce plc Fan containment
CN113446123A (en) * 2020-03-26 2021-09-28 和谐工业有限责任公司 Air turbine starter containment system
EP3885537A1 (en) * 2020-03-26 2021-09-29 Unison Industries LLC Air turbine starter containment system and method of forming such a system

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GB2365925B (en) 2005-02-23
GB0019664D0 (en) 2000-09-27

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