US3602602A - Burst containment means - Google Patents
Burst containment means Download PDFInfo
- Publication number
- US3602602A US3602602A US825724A US3602602DA US3602602A US 3602602 A US3602602 A US 3602602A US 825724 A US825724 A US 825724A US 3602602D A US3602602D A US 3602602DA US 3602602 A US3602602 A US 3602602A
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- Prior art keywords
- winding
- containment means
- fragments
- burst
- housing
- Prior art date
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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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T74/00—Machine element or mechanism
- Y10T74/21—Elements
- Y10T74/219—Guards
Definitions
- the invention relates to a means for containing burst fragments generated when very high speed machinery, particularly gas turbines, rupture.
- the containment means is a winding of tape over the machinery housing and radially aligned along the expected path of travel of part fragments.
- the winding is formed from lightweight material having high strength and high elongation properties providing unusual energy absorbing capabilities which tends to contain the impact of burst fragments primarily by deflection rather than high yield stresses PATENIED was] l97
- the containment means described is used for the purpose of containing burst fragments within a localized area in the event the rotor of a very high speed machine ruptures.
- the invention has immediate application to the compressor section of gas turbines and can be further extended to the turbine section following the development of a high temperature and high elongation plastic fiber such as ahigh temperature nylon known as N orel for example.
- a burst containment means comprises a housing, a winding made up of at least 15 overlying turns of a tape formed from a material having a specific energy absorbing capability of at least 200,000 (lN-LB/LB).
- FIG. 1 is a partial cross-sectional representation of a burst containment means embodying the principles of the present invention
- FIG. 2 is a schematic representation of the winding comprising a portion of the burst containment means
- FlG. 3 is an expanded segmented view of the burst containment means showing structural details
- FIG. 4 is a pictorial representation of the invention in the act of restraining high kinetic energy fragments.
- the energy absorbing capability of a material is determined by reference to a standard stress-strain curve of the material where stress is specified in LB/lN and the strain in lN/lN.
- the energy absorbing capability of a material is determined by calculating the area under the stress-strain curve.
- the specific energy absorbing capability ie the energy that a material can absorb per pound of material, of steel is 121,000 (lN-LB/LB.)
- the specific energy absorbing capability of nylon on the other hand, is 204,000 (IN-LB/LB) and is in fact a preferred candidate material.
- the low strength material is utilized to its fullest capability when it is wound into a coil or winding containing at least 15 turns for reasons that will be explained hereinafter.
- FIG. 1 of the drawings there is illustrated ing cross section the pertinent elements of a gas turbine compressor assembly 10.
- the assembly includes a hub 11 on the circumference of which are fastened a plurality of compressor blades 12.
- a housing 13 formed from any suitable metal material.
- a winding 14 comprising at least 15 turns 16.
- the turns 16 are formed from a continuous length of a material having a specific energy absorbing capability of 200,000 (lN-LB/LB) or greater.
- a nylon ballistic cloth as defined and identified in the Mill Standard specification Mil-(3123690 is the preferred material to use in making up the winding of 14.
- FIG. 2 is a schematic representation showing the use of a continuous tape in making up the winding 14. It also represents schematically that there are no means for bonding or fastening the adjacent turns 16 of the winding 14 to each other or to the housing 13.
- HO. 3 is another representation of the winding structure providing additional detail.
- FIG. 4 of the drawings serves to illustrate why it is important to 1) provide a plurality of turns 16 preferably a minimum of 15 turns, and (2) provide a winding where adjacent turns are free to move relative to each other.
- FIG. 4 illustrates the winding 14 in the process of absorbing three high energy fragments from an exploding mechanical member.
- the housing 11 has been completely shattered and is no longer a factor in containing the fragments.
- the configuration of the winding 14 has changed into an optimum configuration for the type of impact it is resisting.
- the wide center portion 19 of the three legs of the winding indicate that'a number of turns 16 of the winding 14 have failed in tension.
- the high density of turns 16 adjacent to the outside of the winding 14 indicate that a substantial number of turns 16 are compressed and absorbing the energy applied to the winding by the fragments.
- the housing upon rupturing creates secondary high energy fragments but generally these do not pose a serious problem.
- a burst containment means comprising the combination of a housing about a rotated bladed structure, a winding on said housing consisting essentially of at least 15 overlapping turns of a tape formed from a nylon ballistic material having a specific energy absorbing capability of at least 200,000 (lN-LB/LB).
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a means for containing burst fragments generated when very high speed machinery, particularly gas turbines, rupture. The containment means is a winding of tape over the machinery housing and radially aligned along the expected path of travel of part fragments. The winding is formed from lightweight material having high strength and high elongation properties providing unusual energy absorbing capabilities which tends to contain the impact of burst fragments primarily by deflection rather than high yield stresses.
Description
United States Patent 3,203,180 8/1965 Price Inventor Salvatore Motta Lowell, Mass.
App]. No. 825,724
Filed May 19, 1969 Patented Aug. 31,1971
Assignee Avco Corporation Cincinnati, Ohio BURST CONTAINMENT MEANS 2 Claims, 4 Drawing Figs.
U.S. C1 41-5/9, 74/608.415/197,415/214 Int. Cl Fl6p 1/02 Field of Search 74/608,
References Cited UNITED STATES PATENTS 1,698,514 1/1929 Schmidt 74/609 2,848,133 8/1958 Ramberg..... 156/189 2.999.667 9/1961 Morley 230/132 3,272,672 9/1966 Lampman et a1. 156/189 FOREIGN PATENTS 1.013.096 12/1965 Great Britain 415/174 Primary Examiner- Henry F. Raduazo Auorneys-Charles' M. Hoganand and Abraham Ogman ABSTRACT: The invention relates to a means for containing burst fragments generated when very high speed machinery, particularly gas turbines, rupture. The containment means is a winding of tape over the machinery housing and radially aligned along the expected path of travel of part fragments. The winding is formed from lightweight material having high strength and high elongation properties providing unusual energy absorbing capabilities which tends to contain the impact of burst fragments primarily by deflection rather than high yield stresses PATENIED was] l97| 3602.602
I N VENTOR. SALVATORE MOTTA BY M A ORNEY BURST CONTAINMENT MEANS The containment means described is used for the purpose of containing burst fragments within a localized area in the event the rotor of a very high speed machine ruptures. The invention has immediate application to the compressor section of gas turbines and can be further extended to the turbine section following the development of a high temperature and high elongation plastic fiber such as ahigh temperature nylon known as N orel for example.
In the past a metal, usually steel, in a single mass, laminated or woven form has been used. In one respect steel would appear to be an excellent candidate. in practice, particularly in aviation gas turbine applications, it is practically useless for a rather unusual reason, to be demonstrated.
It is an object of the invention to provide a burst containment means for high energy fragments which (i) avoids the limitations and disadvantages of prior art devices, (ii) is lightweight and compact, (iii) made from material which is capable of absorbing at least twice as much kinetic energy as steel of the same weight, (iv) is constructed from a nylon tape material having a high strength to failure ratio, and (v) comprises a winding of at least turns of tape.
in accordance with the invention a burst containment means comprises a housing, a winding made up of at least 15 overlying turns of a tape formed from a material having a specific energy absorbing capability of at least 200,000 (lN-LB/LB).
The novel features that are considered characteristic of the invention are set forth in the appended claims; the invention itself, however, both as to its organization and method of operation, together with additional objects and advantages thereof, will best be understood from the followingdescription of a specific embodiment when read in conjunction with the accompanying drawings, in which:
FIG. 1 is a partial cross-sectional representation of a burst containment means embodying the principles of the present invention;
FIG. 2 is a schematic representation of the winding comprising a portion of the burst containment means;
FlG. 3 is an expanded segmented view of the burst containment means showing structural details; and
FIG. 4 is a pictorial representation of the invention in the act of restraining high kinetic energy fragments.
The energy absorbing capability ofa material is determined by reference to a standard stress-strain curve of the material where stress is specified in LB/lN and the strain in lN/lN. The energy absorbing capability ofa material is determined by calculating the area under the stress-strain curve.
in tests conducted on a nylon ballistic cloth material the energy absorbing capability of the material was determined to be 8,000 (lN-LB/lN). The energy absorbing capability of steel that was considered suitable for fragment containment was determined to be 35,000 (lN-LB/lN it would appear from the foregoing that steel is much more suited for fragment containment than the nylon cloth. The fact of the matter is, however, that it is, from a practical point of view, much worse. For one thing, steel, because it has a high modulus of elasticity, tends to resist an impact with negligible deflection and consequently it tends to shatter rather than absorb energy.
Another very serious limitation of steel is its weight. For example, the specific energy absorbing capability, ie the energy that a material can absorb per pound of material, of steel is 121,000 (lN-LB/LB.) The specific energy absorbing capability of nylon, on the other hand, is 204,000 (IN-LB/LB) and is in fact a preferred candidate material.
The low strength material is utilized to its fullest capability when it is wound into a coil or winding containing at least 15 turns for reasons that will be explained hereinafter.
Referring to FlG. 1 of the drawings there is illustrated ing cross section the pertinent elements of a gas turbine compressor assembly 10. The assembly includes a hub 11 on the circumference of which are fastened a plurality of compressor blades 12. Surrounding and spaced from the compressor blades 12 is a housing 13 formed from any suitable metal material.
Lapped around the housing 13 is a winding 14 comprising at least 15 turns 16.
The turns 16 are formed from a continuous length of a material having a specific energy absorbing capability of 200,000 (lN-LB/LB) or greater. A nylon ballistic cloth as defined and identified in the Mill Standard specification Mil-(3123690 is the preferred material to use in making up the winding of 14.
FIG. 2 is a schematic representation showing the use of a continuous tape in making up the winding 14. It also represents schematically that there are no means for bonding or fastening the adjacent turns 16 of the winding 14 to each other or to the housing 13.
HO. 3 is another representation of the winding structure providing additional detail.
FIG. 4 of the drawings serves to illustrate why it is important to 1) provide a plurality of turns 16 preferably a minimum of 15 turns, and (2) provide a winding where adjacent turns are free to move relative to each other. FIG. 4 illustrates the winding 14 in the process of absorbing three high energy fragments from an exploding mechanical member. The housing 11 has been completely shattered and is no longer a factor in containing the fragments. The configuration of the winding 14 has changed into an optimum configuration for the type of impact it is resisting. The wide center portion 19 of the three legs of the winding indicate that'a number of turns 16 of the winding 14 have failed in tension. The high density of turns 16 adjacent to the outside of the winding 14 indicate that a substantial number of turns 16 are compressed and absorbing the energy applied to the winding by the fragments.
it is clear that the amount of energy that is to be contained will vary with the speed and the configuration of the high energy fragments. The primary use of the housing relates to its function in connection with the gas turbine compressor. Its very presence causes it to absorb some of the energy from fragments; but because it is made of metal and because its thickness is determined by the gas turbine performance, it is not a' good energy absorber and in fact the major portion of the energy contained in a fragment is absorbed by the winding 14. On occasion it has been noted that the housing upon rupturing creates secondary high energy fragments but generally these do not pose a serious problem.
A number of tests have been made by preparing a 3-inch wide winding over an 18-inch diameter housing. Each turn was one thirty-second inch thick and 33% turns were used to make up the complete winding. This particular design has successfully resisted impact up to and including 83,500 IN-lbs. Up to 40 percent of the turns experienced one or more breaks. These breaks were examined and were determined to be tension breaks. The intact" turns underwent appreciable elon' gation. High energy fragments were completely contained in the windings.
The various features and advantages of the invention are thought to be clear from the foregoing description. Various other features and advantages not specifically enumerated will undoubtedly occur to those versed in the art, as likewise will many variations and modifications of the preferred embodiment illustrated, all of which may be achieved without departing from the spirit and scope of the invention as defined by the following claims:
1. A burst containment means comprising the combination of a housing about a rotated bladed structure, a winding on said housing consisting essentially of at least 15 overlapping turns of a tape formed from a nylon ballistic material having a specific energy absorbing capability of at least 200,000 (lN-LB/LB).
2. A burst containment means as defined in claim 1 in which the winding is formed from a woven tape of a nylon ballistic material.
Claims (2)
1. A burst containment means comprising the combination of a housing about a rotated bladed structure, a winding on said housing consisting essentially of at least 15 overlapping turns of a tape formed from a nylon ballistic material having a specific energy absorbing capability of at least 200,000 (INLB/LB).
2. A burst containment means as defined in claim 1 in which the winding is formed from a woven tape of a nylon ballistic material.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US82572469A | 1969-05-19 | 1969-05-19 |
Publications (1)
Publication Number | Publication Date |
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US3602602A true US3602602A (en) | 1971-08-31 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US825724A Expired - Lifetime US3602602A (en) | 1969-05-19 | 1969-05-19 | Burst containment means |
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Cited By (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3936219A (en) * | 1974-06-10 | 1976-02-03 | Westinghouse Electric Corporation | Flexible turbine missile shield |
US3949711A (en) * | 1974-02-08 | 1976-04-13 | Stackpole Carbon Company | Rotary engine with graphite housing |
US4057359A (en) * | 1975-12-22 | 1977-11-08 | Chevron Research Company | Ballistic nylon fabric turbine governor housing shielding means |
US4149824A (en) * | 1976-12-23 | 1979-04-17 | General Electric Company | Blade containment device |
FR2444800A1 (en) * | 1978-12-21 | 1980-07-18 | Rolls Royce | Gas turbine protective ring - has reinforced polyamide fibre material layers wrapped on carrier ring |
FR2448626A1 (en) * | 1979-02-08 | 1980-09-05 | Snecma | IMPROVEMENT IN ROTORS OF ROTATING MACHINES |
EP0027756A1 (en) * | 1979-10-19 | 1981-04-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Safety device in case of rupture of a rotating turbomachine part |
FR2467978A1 (en) * | 1979-10-23 | 1981-04-30 | Snecma | RETENTION DEVICE FOR A COMPRESSOR CASE OF A TURBOMACHINE |
US4304633A (en) * | 1975-10-24 | 1981-12-08 | Hitachi, Ltd. | Nuclear power plant |
FR2514823A1 (en) * | 1981-10-16 | 1983-04-22 | Poudres & Explosifs Ste Nale | Guard to protect against centrifugal rupture of high speed rotor - esp. aircraft gas turbine, uses sheet of fibres impregnated with organic resin |
FR2518648A1 (en) * | 1981-12-21 | 1983-06-24 | United Technologies Corp | METHOD FOR FORMING A CONTAINMENT STRUCTURE AND A CONTAINMENT STRUCTURE, IN PARTICULAR FOR A ROTARY MACHINE |
US4452565A (en) * | 1981-12-21 | 1984-06-05 | United Technologies Corporation | Containment structure |
US4475864A (en) * | 1981-12-21 | 1984-10-09 | United Technologies Corporation | Containment structure |
US4699567A (en) * | 1984-06-07 | 1987-10-13 | Rolls-Royce Plc | Fan duct casing |
US4718818A (en) * | 1981-12-21 | 1988-01-12 | United Technologies Corporation | Containment structure |
US4746150A (en) * | 1983-06-09 | 1988-05-24 | Nitro Nobel Ab | Joint for joining together two pipe ends |
US4786231A (en) * | 1986-12-01 | 1988-11-22 | Kelley Winfield L | Noise attenuating and air streamlining spiral |
US4818176A (en) * | 1987-04-15 | 1989-04-04 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Burst guard ring for turbo-engine housings |
US4961685A (en) * | 1988-09-06 | 1990-10-09 | Mtu-Motoren-Und Turbinen-Union Muenchen Gmbh | Protection ring of fiber material for containing fragments of bursting structural components |
US5163809A (en) * | 1991-04-29 | 1992-11-17 | Pratt & Whitney Canada, Inc. | Spiral wound containment ring |
DE4223496A1 (en) * | 1992-07-17 | 1994-01-20 | Asea Brown Boveri | Reducing kinetic energy of bursting parts in turbines - involves crumple zone between inner and outer rings set between housing and rotor to absorb energy and contain fractured parts |
US5328324A (en) * | 1991-12-14 | 1994-07-12 | Rolls-Royce Plc | Aerofoil blade containment |
EP0718471A1 (en) * | 1994-12-21 | 1996-06-26 | Hispano-Suiza | Containment ring for a turbomachine |
US5614280A (en) * | 1993-12-02 | 1997-03-25 | James W. Post, III | Shielding blanket for racing engines |
US6059523A (en) * | 1998-04-20 | 2000-05-09 | Pratt & Whitney Canada Inc. | Containment system for containing blade burst |
US6182531B1 (en) | 1998-06-12 | 2001-02-06 | The Boeing Company | Containment ring for flywheel failure |
US20050025615A1 (en) * | 2003-07-30 | 2005-02-03 | The Boeing Company | High energy containment device and turbine with same |
US20050188777A1 (en) * | 2004-02-26 | 2005-09-01 | Wingett Paul T. | Energy storage flywheel system containment vessel |
US20050241208A1 (en) * | 2004-04-29 | 2005-11-03 | Ditchfield Bradley J | Portable ballistic unloading device |
US20060165519A1 (en) * | 2005-01-21 | 2006-07-27 | Mcmillan Alison J | Aerofoil containment structure |
US20080105114A1 (en) * | 2003-07-30 | 2008-05-08 | The Boeing Company | Composite containment of high energy debris and pressure |
US20080115454A1 (en) * | 2006-11-21 | 2008-05-22 | Ming Xie | Methods for reducing stress on composite structures |
US20090269197A1 (en) * | 2008-04-28 | 2009-10-29 | Rolls-Royce Plc | Fan Assembly |
US20110083433A1 (en) * | 2009-10-14 | 2011-04-14 | Peter Stroph | Explosion protection for a turbine and combustion engine |
US20120039703A1 (en) * | 2010-08-12 | 2012-02-16 | Kendall Swenson | Fragment containment assembly and method for adding a fragment containment assembly to a turbine |
US20120102912A1 (en) * | 2010-10-27 | 2012-05-03 | Said Izadi | Low cost containment ring |
US20160053632A1 (en) * | 2014-08-21 | 2016-02-25 | Honeywell International Inc. | Fan containment cases for fan casings in gas turbine engines, fan blade containment systems, and methods for producing the same |
CN105822891A (en) * | 2016-03-18 | 2016-08-03 | 苏州东菱科技有限公司 | High-speed rotation protective device |
US10487684B2 (en) | 2017-03-31 | 2019-11-26 | The Boeing Company | Gas turbine engine fan blade containment systems |
US10550718B2 (en) | 2017-03-31 | 2020-02-04 | The Boeing Company | Gas turbine engine fan blade containment systems |
US11391297B2 (en) * | 2017-11-09 | 2022-07-19 | Pratt & Whitney Canada Corp. | Composite fan case with nanoparticles |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
US11512646B2 (en) | 2019-12-23 | 2022-11-29 | Unison Industries, Llc | Air starter with bearing cooling |
US11549442B2 (en) | 2020-03-26 | 2023-01-10 | Unison Industries, Llc | Air turbine starter containment system |
US20230340890A1 (en) * | 2022-04-21 | 2023-10-26 | Pratt & Whitney Canada Corp. | Multi-layered containment structure for a bladed rotor of a gas turbine engine |
-
1969
- 1969-05-19 US US825724A patent/US3602602A/en not_active Expired - Lifetime
Cited By (64)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3949711A (en) * | 1974-02-08 | 1976-04-13 | Stackpole Carbon Company | Rotary engine with graphite housing |
US3936219A (en) * | 1974-06-10 | 1976-02-03 | Westinghouse Electric Corporation | Flexible turbine missile shield |
US4304633A (en) * | 1975-10-24 | 1981-12-08 | Hitachi, Ltd. | Nuclear power plant |
US4057359A (en) * | 1975-12-22 | 1977-11-08 | Chevron Research Company | Ballistic nylon fabric turbine governor housing shielding means |
US4149824A (en) * | 1976-12-23 | 1979-04-17 | General Electric Company | Blade containment device |
FR2444800A1 (en) * | 1978-12-21 | 1980-07-18 | Rolls Royce | Gas turbine protective ring - has reinforced polyamide fibre material layers wrapped on carrier ring |
FR2448626A1 (en) * | 1979-02-08 | 1980-09-05 | Snecma | IMPROVEMENT IN ROTORS OF ROTATING MACHINES |
EP0027756A1 (en) * | 1979-10-19 | 1981-04-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Safety device in case of rupture of a rotating turbomachine part |
FR2467977A1 (en) * | 1979-10-19 | 1981-04-30 | Snecma | SAFETY DEVICE IN THE EVENT OF TURBOMACHINE ROTATING ELEMENT BREAK |
US4377370A (en) * | 1979-10-19 | 1983-03-22 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Safety device for a rotating element of a turbine engine |
FR2467978A1 (en) * | 1979-10-23 | 1981-04-30 | Snecma | RETENTION DEVICE FOR A COMPRESSOR CASE OF A TURBOMACHINE |
EP0028183A1 (en) * | 1979-10-23 | 1981-05-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Containment device for the compressor housing of a turbomachine |
FR2514823A1 (en) * | 1981-10-16 | 1983-04-22 | Poudres & Explosifs Ste Nale | Guard to protect against centrifugal rupture of high speed rotor - esp. aircraft gas turbine, uses sheet of fibres impregnated with organic resin |
US4718818A (en) * | 1981-12-21 | 1988-01-12 | United Technologies Corporation | Containment structure |
US4452565A (en) * | 1981-12-21 | 1984-06-05 | United Technologies Corporation | Containment structure |
US4475864A (en) * | 1981-12-21 | 1984-10-09 | United Technologies Corporation | Containment structure |
FR2518648A1 (en) * | 1981-12-21 | 1983-06-24 | United Technologies Corp | METHOD FOR FORMING A CONTAINMENT STRUCTURE AND A CONTAINMENT STRUCTURE, IN PARTICULAR FOR A ROTARY MACHINE |
DE3243887A1 (en) * | 1981-12-21 | 1983-06-30 | United Technologies Corp., 06101 Hartford, Conn. | MANUFACTURING METHOD FOR A PARTICLE COLLECTOR, ESPECIALLY A PROTECTIVE HOUSING, PROTECTIVE COATING APPLICATION PROCESS AND PROTECTIVE DEVICE |
US4746150A (en) * | 1983-06-09 | 1988-05-24 | Nitro Nobel Ab | Joint for joining together two pipe ends |
US4699567A (en) * | 1984-06-07 | 1987-10-13 | Rolls-Royce Plc | Fan duct casing |
US4786231A (en) * | 1986-12-01 | 1988-11-22 | Kelley Winfield L | Noise attenuating and air streamlining spiral |
US4818176A (en) * | 1987-04-15 | 1989-04-04 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Burst guard ring for turbo-engine housings |
US4961685A (en) * | 1988-09-06 | 1990-10-09 | Mtu-Motoren-Und Turbinen-Union Muenchen Gmbh | Protection ring of fiber material for containing fragments of bursting structural components |
US5163809A (en) * | 1991-04-29 | 1992-11-17 | Pratt & Whitney Canada, Inc. | Spiral wound containment ring |
US5328324A (en) * | 1991-12-14 | 1994-07-12 | Rolls-Royce Plc | Aerofoil blade containment |
DE4223496A1 (en) * | 1992-07-17 | 1994-01-20 | Asea Brown Boveri | Reducing kinetic energy of bursting parts in turbines - involves crumple zone between inner and outer rings set between housing and rotor to absorb energy and contain fractured parts |
US5614280A (en) * | 1993-12-02 | 1997-03-25 | James W. Post, III | Shielding blanket for racing engines |
EP0718471A1 (en) * | 1994-12-21 | 1996-06-26 | Hispano-Suiza | Containment ring for a turbomachine |
WO1996019641A1 (en) * | 1994-12-21 | 1996-06-27 | Societe Hispano Suiza | Protective shield for a turbomachine |
US6059523A (en) * | 1998-04-20 | 2000-05-09 | Pratt & Whitney Canada Inc. | Containment system for containing blade burst |
US6182531B1 (en) | 1998-06-12 | 2001-02-06 | The Boeing Company | Containment ring for flywheel failure |
US20050025615A1 (en) * | 2003-07-30 | 2005-02-03 | The Boeing Company | High energy containment device and turbine with same |
US20080105114A1 (en) * | 2003-07-30 | 2008-05-08 | The Boeing Company | Composite containment of high energy debris and pressure |
US7954418B2 (en) | 2003-07-30 | 2011-06-07 | The Boeing Company | Composite containment of high energy debris and pressure |
US7008173B2 (en) | 2003-07-30 | 2006-03-07 | The Boeing Company | High energy containment device and turbine with same |
US20100095832A1 (en) * | 2003-07-30 | 2010-04-22 | The Boeing Company | Composite containment of high energy debris and pressure |
US7597040B2 (en) | 2003-07-30 | 2009-10-06 | The Boeing Company | Composite containment of high energy debris and pressure |
US20050188777A1 (en) * | 2004-02-26 | 2005-09-01 | Wingett Paul T. | Energy storage flywheel system containment vessel |
US7111522B2 (en) * | 2004-02-26 | 2006-09-26 | Honeywell International, Inc. | Energy storage flywheel system containment vessel |
US20050241208A1 (en) * | 2004-04-29 | 2005-11-03 | Ditchfield Bradley J | Portable ballistic unloading device |
US7604199B2 (en) * | 2005-01-21 | 2009-10-20 | Rolls-Royce Plc | Aerofoil containment structure |
US20060165519A1 (en) * | 2005-01-21 | 2006-07-27 | Mcmillan Alison J | Aerofoil containment structure |
US8966754B2 (en) * | 2006-11-21 | 2015-03-03 | General Electric Company | Methods for reducing stress on composite structures |
US20080115454A1 (en) * | 2006-11-21 | 2008-05-22 | Ming Xie | Methods for reducing stress on composite structures |
US20090269197A1 (en) * | 2008-04-28 | 2009-10-29 | Rolls-Royce Plc | Fan Assembly |
US8057171B2 (en) * | 2008-04-28 | 2011-11-15 | Rolls-Royce, Plc. | Fan assembly |
US8528328B2 (en) * | 2009-10-14 | 2013-09-10 | Mtu Friedrichshafen Gmbh | Explosion protection for a turbine and combustion engine |
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