GB2391267A - Frangible coupling - Google Patents
Frangible coupling Download PDFInfo
- Publication number
- GB2391267A GB2391267A GB0313659A GB0313659A GB2391267A GB 2391267 A GB2391267 A GB 2391267A GB 0313659 A GB0313659 A GB 0313659A GB 0313659 A GB0313659 A GB 0313659A GB 2391267 A GB2391267 A GB 2391267A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- ligaments
- frangible coupling
- coupling
- ligament
- 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
Links
- 230000008878 coupling Effects 0.000 title claims abstract description 44
- 238000010168 coupling process Methods 0.000 title claims abstract description 44
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 44
- 210000003041 ligament Anatomy 0.000 claims abstract description 56
- 230000001965 increasing effect Effects 0.000 claims description 9
- 238000004891 communication Methods 0.000 claims description 5
- 230000002159 abnormal effect Effects 0.000 abstract description 4
- 239000003570 air Substances 0.000 description 11
- 230000003068 static effect Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- 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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D9/00—Couplings with safety member for disconnecting, e.g. breaking or melting member
- F16D9/06—Couplings with safety member for disconnecting, e.g. breaking or melting member by breaking due to shear stress
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16P—SAFETY DEVICES IN GENERAL; SAFETY DEVICES FOR PRESSES
- F16P5/00—Emergency means for rendering ineffective a coupling conveying reciprocating movement if the motion of the driven part is prematurely resisted
- F16P5/005—Overload protection by energy absorbing components, e.g. breaker blocks, shear sections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/30—Retaining components in desired mutual position
- F05B2260/301—Retaining bolts or nuts
- F05B2260/3011—Retaining bolts or nuts of the frangible or shear type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
- F16B2200/63—Frangible connections
Abstract
A frangible coupling 12 comprises first 40 and second 44 rings joined via an array of ligaments 42. The ligaments 42 are configured to fail when an abnormal radial load of a predetermined value causes relative movement of the first 40 and second 44 rings. The first ring 40, which may be coaxial with the second 44, may be formed with a flange 46 and the ligaments 42 may be axially aligned and formed with a stress raising feature 50 in the region where they contact the flange 46 upon relative movement of the rings 40, 44. A further embodiment includes a rotatable member (62, Fig 5) which, upon contact with the ligaments 42, causes their failure. The coupling may be used to support the shaft of a gas turbine driven fan.
Description
1 - 239 1 267
FRANGIBLE COUPLING
The invention relates to a frangible coupling. In particular it refers to a frangible coupling for turbo machinery.
In a conventional gas turbine engine, the fan is used for pressurising ambient air which then passes downstream to a compressor to be further compressed. The air is then mixed with fuel in a combustor, ignited and burned to expand the gas, further increasing the gas pressure before exhausting via a turbine from which energy is extracted. The engine may have a high pressure turbine which powers the compressor, and a low pressure turbine which powers the fan.
Other engines utilise power off takes, perhaps directly from one of the turbine stages, to drive independent fans to generate propulsive thrust remote from the propulsion unit.
The fan typically comprises an annular array of large fan blade rotors that extend radially outward from a supporting disc. The fan is fixedly joined to a shaft and is rotatable about the axis of the shaft, which is rotatably supported by a number of bearings in communication with a static fan support structure. The concentric alignment of the fan within a surrounding fan casing is maintained by the bearings. The bearings also act as a means to transmit aerodynamic, centrifugal and vibratory loads into the fan support structure. During normal operation the fan is dynamically balanced.
In the rare event of the loss of a section of a blade, perhaps because of foreign object damage or failure of the rotor blade material, there may be a substantial rotary imbalance introduced into the fan system. This will be transmitted to the fan support structure. If the engine is fitted to an aircraft, this may lead to undesirable vibrations being transmitted to the airframe body. In extreme cases the aircraft may become difficult to handle or suffer severe structural damage.
The engine may be turned off to prevent unnecessary damage to itself and the airframe. However, whilst in flight, there may be no means to stop the aerodynamic
( - 2 windmilling of the damaged engine, which may be enough to cause a substantial imbalanced load and further damage.
Likewise, if the fan is driven remotely from the engine it may be desirable to run the damaged fan to generate propulsion. A common requirement is to be able to run the fan up to a predetermined imbalance load, thereby coping with a proportion of blade loss. The fan should only be taken out of use when the imbalance load reaches a certain unacceptable level. It may not be possible for a pilot to make this judgement, requiring some safety feature of the fan to sever the connection between the imbalanced load and the fan structure.
In order to accommodate the possibility of such abnormal radial loads the supporting components for the fan may be strengthened. This may have the undesirable effect of increasing the size, weight and expense of the fan structure. Means for the controlled buckling of various parts of engine structure have also been utilised.
Another solution is the introduction of a coupling placed between the bearing support
structure and the fan support structure that de-couples when the imbalance reaches a predetermined level. Such a device is frequently referred to as a structural fuse or a frangible coupling. When decoupled the connection between the bearing support and support structure is severed, leaving the fan supported by its shaft and at one end by a bearing. Conventional structural fuses are designed to de-couple above relatively low abnormal radial loads. However, an increasingly common requirement is for the fan to carry on rotating and generating useful thrust with a degree of out of balance loading.
The fuse has two conflicting requirements. It must withstand any fatigue or normal operational loads but fail reliably under the increased fan blade off load. This presents a load range within which the fuse must be designed. The extra requirement that the fuse not fail under partial fan blade off but fail under full blade off makes the design window prohibitively narrow.
( Fuse designs exist that utilise shear bolts and spigots that fasten the supporting components of the fan together. However, given the tolerances inherent in the design and materials used, it is not possible to define accurately at what load the fuse will severe the connection. Hence the fuse may sever the connection when the imbalance is below the required lower level, resulting in premature decoupling, or above the higher level, resulting in damage to the fan structure, engine or aircraft.
According to the present invention there is provided a frangible coupling comprising a first ring and a second ring interconnected by a plurality of ligaments, said ligaments configured to fail when a load of a predetermined value causes the first and second ring to move relative to one another by a predetermined amount.
Preferably the first ring is formed with a flange that is provided with a plurality of semi-
circular cross-section cut out portions each of which corresponds closely to the outside diameter of the ligaments part way along the ligaments, there being a small clearance maintained between the ligaments and their corresponding cut out portions in the flange. Preferably at least one ligament is formed with a stress raising feature in the region where it is designed to contact the flange when a load of a predetermined value causes the first and second ring to move relative to one another by a predetermined amount.
Preferably the frangible coupling is configured such that at a predetermined out of balance loading induced by the rotatable load at least one ligament is brought into contact with the flange, thereby increasing the stress concentration in the at least one ligament to a level where the at least one ligament fails.
The invention provides an internal support structure for rotatable turbo machinery components that will fail when subjected to out of balance forces imparted to the structure caused by a fan blade off or partial fan blade off. The stress raising feature within the fuse accelerates the fracture process, breaking the fuse within a narrower
( -4 and predictable loading range. This allows the rotor to orbit closer to its new centre of gravity and either transmit a reduced load by a secondary route, or removes the load path altogether.
In commonly used aerospace metals there is a linear relationship between load applied I and stress induced. This invention employs a means whereby when the load raises to: a certain level, the rate of change of stress in the material suddenly is increased, inducing fracture within a much smaller and predictable load range. The stresses acting on the ligaments are magnified, causing them to fail at lower loads than they otherwise would.
This load magnification at high loads enables the ligaments to be designed for a long fatigue life at low loads whilst failing positively at higher loads.
The invention and how it may be constructed and operated, will now be described in greater detail with reference, by way of example, to an embodiment illustrated in the accompanying drawings, in which: Figure 1 is a pictorial representation of a typical gas turbine engine; Figure 2 is a pictorial representation of a fan powered remotely from an engine; Figure 3 shows a schematic representation of the relevant section of a fan, illustrating the location of the frangible coupling relative to the rotatable components; Figure 4 shows a first embodiment of the frangible coupling; Figure 5 shows a second ennbodiment of the frangible coupling; Figure 6 shows the second embodiment distorted by an out of balance force, the distortion is exaggerated for clarity; and
- 5 Figure 7 is a diagrammatic representation of the relationship between load applied and stress induced in the frangible coupling.
Figure 1 illustrates the main sections of a gas turbine engine 2. The overall construction and operation of the engine 2 is of a conventional kind, well known in the field, and will not be described in this specification beyond that necessary to gain an
understanding of the invention. For the purposes of this description the engine is
divided up into four sections - a fan section 4, a compressor section 6, a combustor section 8 and a turbine section 10. Air, indicated generally by arrow "A", enters the engine 2 via the fan section 4. The air is compressed and moves downstream to the compressor 6. This further pressurises the air, a proportion of which enters the combustion section 8, the remainder of the air being employed elsewhere. Fuel is injected into the combustor airflow, which mixes with air and ignites before exhausting out of the rear of the engine, indicated generally by arrow "B", via the turbine section 10. A cutaway reveals the location of a frangible coupling 12.
Figure 2 illustrates a fan unit 14 that is driven remotely from an engine. It does not provide compressed air to the engine but is used to generate propulsive thrust remote from the propulsion unit. In figure 2 the fan unit 14 is shown mounted with its central axis vertical. This is only one embodiment, drawn here for illustrative purposes. The fan unit may be mounted in any orientation.
For the purposes of this description the fan unit 14 is divided up into 3 sections - a fan
rotor section 16, a compressor section 18 and a drive shaft and gearing arrangement 20, the latter being shown in a cutaway view. Air, indicated generally by arrow "C", enters the fan unit 14 via the fan rotor section 16. The air is compressed and moves downstream to compressor 18, where it is further pressurised before being exhausted from the fan 14, indicated generally by arrow "B". A cutaway reveals the location of the frangible coupling 12.
An enlarged view of fan assembly common to the engine 2 and fan unit 14 is presented in Figure 3. Air, indicated generally by arrow "E", enters the fan unit 14, constrained on
- 6 one side by an outer wall 22 and on the other by a discontinuous inner wall 24. Support for the inner wall 24 is provided by an array of support members 25 which extend radially towards, and are in communication with, the outer wall 22. The inner wall 24 comprises several static and rotatable sections, the details of which are not required here to appreciate the invention. The air is pressurised by an annular array of fan rotor blades 26 and then passes downstream, as indicated generally by arrow "F".
The fan blades 26 are fixedly joined to a shaft 28 that is rotatable about the central axis of the fan unit 14. The shaft 28 is rotabably supported by bearings 30 and 32 at the downstream and upstream ends respectively. The bearing 32 is supported by the non-
rotatable frangible coupling 12 via a first static member 36. The coupling 12 is in communication with a non-rotatable section of the inner wall 24 via a second static member 38.
Figure 4 shows an enlarged view of the frangible coupling 12, with the first member 36 and second member 38 removed for clarity. The frangible coupling 12 comprises a first ring 40 axially joined via a row of generally circular cross section fuse ligaments 42 to a second ring 44.
The first ring 40 is formed with a flange 46 that is provided with semicircular cross-
section cut out portions 43 that correspond closely to the outside diameter of the ligaments 42 part way along their length. A small clearance 48 is maintained between the ligaments 42 and their corresponding cut out portions 43 in the flange 46. The fuse ligaments 42 are equidistantly spaced apart from each other and are formed with a stress raising feature 50, which, as shown here, may take the form of a narrowed waist.
In normal use the primary load path from the fan shaft 28 is through the support bearing 32, and then through the coupling 12 to the inner wall 24, transmitted then to the support members 25 which communicate it to the outer wall 22.
Under high out of balance loads the ligaments 42 deflect, the clearance 48 closes and the flange 46 forms part of the secondary load path. A consequence of the out of
balance nature of the loading is that the ligament 42 in contact with the flange 46 will carry significantly more load than the other ligaments. This results in the rapid failure of the ligament 42 in contact with the flange 46. Since the applied load is rotating the adjacent ligament 42 quickly becomes loaded in a similar way and also fails. This process is repeated until all of the ligaments 42 have failed. With the ligaments 42 severed, the first ring 40 is free to move independently of the second ring 44, allowing the out of balance shaft 28 to oscillate about a new axis, which will result in less damage to the engine support casing than if the out of balance force was transmitted through to the inner wall 24.
Figure 5 presents an alternative embodiment of the frangible coupling 12. The coupling 12 comprises a first ring 50 axially joined via a row of fuse ligaments 52 to a second ring 54. The second ring 54 is formed with a third static member 56 (not shown) that is fixedly joined with a non rotatable section of the inner wall 24 (not shown in this figure).
The first ring 50 is fitted with a bearing 58 that rotatably supports the first ring 50 on a shaft 60. The shaft 60 supports the fan blades 26 (not shown in this figure). The shaft 60 is provided with a disc 62 positioned at about one half of the way between the first ring 50 and the second ring 54. Extending radially outward from the circumference of the disc 62 is a snub 64.
In normal in balance operation the blades 26 rotate and cause only small deflections of the shaft 60. When subjected to abnormally high radial loads the shaft 60 will oscillate, transmitting the oscillation to the bearing 58 and the first ring 50, causing the ligaments 52 to deflect, as shown in figure 6 (exaggerated). The relative movement of the ligaments 52 and the snub 64 causes them to impact each other as the snub 64 rotates. The impact is sufficient to cause the failure of the ligaments 52. The first ring 50 will be forced to oscillate with the rotating out of balance load, resulting in the snub 64 impacting on all of the fuse ligaments 52, breaking them in turn and ultimately severing the connection between the first ring 50 and the second ring 54. This allows the first ring 50 to move independently of the second ring 54, allowing the out of balance shaft 60 to oscillate about its new axis, resulting in less damage to the support
- 8 casing of the fan unit 14 than if the out of balance force was transmitted through to the inner wall 24.
During normal operation in both embodiments the fuse ligaments 52 experience an increase in stress proportional to the load imposed by the rotating load. This is indicated by section "G" of the graph in Figure 7. When an abnormal radial load is applied the stress is increased locally in at least one of the fuse ligaments 52, increasing the stress per unit force at the critical location on the ligament 52, indicated by section "H" on the graph. Hence the overall relationship between the load imparted to the first ring 40,50 and stress induced in the fuse ligaments 52 is non linear. The sudden increase in fuse ligament stress enables a better control over the loading at which the ligament 52 will fail.
The failure of some, but not all, of the ligaments 52 may enable the coupling 12 to accommodate the out of balance load where the more rigid structure provided by the coupling 12, when all ligaments 52 are intact, would not sufficiently dampen the excessive oscillation.
The configurations shown in Figures 1, 2, 3, 4, 5 and 6 are diagrammatic. The design and positioning of the frangible coupling, rotor blades, bearings, fan casing and other parts may vary. Likewise the combination and configuration of these components will vary between designs. The relationship presented in Figure 7 is an approximation.
Claims (16)
1 A frangible coupling comprising a first ring and a second ring interconnected by a plurality of ligaments, said ligaments configured to fail when a load of a predetermined value causes the first and second ring to move relative to one another by a predetermined amount.
2 A frangible coupling as claimed in claim 1 wherein the said ligaments are substantially axially aligned.
3 A frangible coupling as claimed claim 1 or claim 2 wherein the first and second rings are cylindrical.
4 A frangible coupling as claimed in any one of the preceding claims wherein the ligaments are equidistantly spaced apart.
5 A frangible coupling as claimed in any one of the preceding claims wherein the first ring and the second ring are coaxial.
6 A frangible coupling as claimed in any one of the preceding claims wherein the first ring and the second ring are concentric.
7 A frangible coupling as claimed in any one of the preceding claims wherein the first ring is formed with a flange that is provided with a plurality of semi-circular cross-section cut out portions each of which corresponds closely to the outside diameter of the ligaments part way along the ligaments, there being a small clearance maintained between the ligaments and their corresponding cut out portions in the flange.
8 A frangible coupling as claimed in claim 7 wherein at least one ligament is formed with a stress raising feature in the region where it is designed to contact
- 10 the flange when a load of a predetermined value causes the first and second ring to move relative to one another by a predetermined amount.
9 A frangible coupling as claimed in any one of the preceding claims wherein each of the ligaments have at least one waisted section.
10 A frangible coupling as claimed in any one the preceding claims wherein the first ring is in communication with a means for supporting a rotatable load.
11 A frangible coupling as claimed in any one of the preceding claims wherein the second ring is fixedly joined to a fan support structure.
12 A frangible coupling as claimed in claims 10 or 11 wherein said frangible coupling is configured such that at a predetermined out of balance loading induced by the rotatable load at least one ligament is brought into contact with the flange, thereby increasing the stress concentration in the at least one ligament to a level where the at least one ligament fails.
13 A frangible coupling as claimed in claim 6 wherein a rotatable shaft is in communication with said first ring via a bearing support means, said rotatable shaft being fixedly joined to a rotatable member positioned between and coaxially with the first and second ring, there being a small clearance maintained between the said member and the ligaments adjacent thereto.
14 A frangible coupling as claimed in claim 13 wherein the coupling is configured such that when the first and second ring to move relative to one another by a predetermined amount said rotatable member will come into contact with at least one ligament thereby increasing the stress concentration in the at least one ligament to a level where the at least one ligament fails.
15 A frangible coupling as claimed in claim 13 and claim 14 wherein the rotatable member is a disc formed with at least one snub which extends substantially
- 11 radially outward from member, there being a small clearance maintained between the said snub and the ligaments adjacent thereto.
16 A frangible coupling substantially as hereinbefore described with reference to the accompanying drawings.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0216312.9A GB0216312D0 (en) | 2002-07-12 | 2002-07-12 | Frangible coupling |
Publications (3)
Publication Number | Publication Date |
---|---|
GB0313659D0 GB0313659D0 (en) | 2003-07-16 |
GB2391267A true GB2391267A (en) | 2004-02-04 |
GB2391267B GB2391267B (en) | 2005-02-16 |
Family
ID=9940400
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GBGB0216312.9A Ceased GB0216312D0 (en) | 2002-07-12 | 2002-07-12 | Frangible coupling |
GB0313659A Expired - Fee Related GB2391267B (en) | 2002-07-12 | 2003-06-12 | Frangible coupling |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GBGB0216312.9A Ceased GB0216312D0 (en) | 2002-07-12 | 2002-07-12 | Frangible coupling |
Country Status (4)
Country | Link |
---|---|
US (1) | US7025560B2 (en) |
EP (1) | EP1382805B1 (en) |
DE (1) | DE60306853T2 (en) |
GB (2) | GB0216312D0 (en) |
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US6886343B2 (en) * | 2003-01-15 | 2005-05-03 | General Electric Company | Methods and apparatus for controlling engine clearance closures |
FR2877994B1 (en) * | 2004-11-17 | 2009-07-10 | Snecma Moteurs Sa | BEARING SUPPORT, AND AIRCRAFT ENGINE EQUIPPED WITH SUCH A BEARING SUPPORT. |
GB2444935B (en) * | 2006-12-06 | 2009-06-10 | Rolls Royce Plc | A turbofan gas turbine engine |
US8122781B2 (en) * | 2007-11-02 | 2012-02-28 | Honeywell International, Inc. | Generator shear gear |
US20090257868A1 (en) * | 2008-04-09 | 2009-10-15 | Giusto Fonda-Bonardi | Diffuser |
GB0815482D0 (en) * | 2008-08-27 | 2008-10-01 | Rolls Royce Plc | A blade and method of making a blade |
GB0815483D0 (en) * | 2008-08-27 | 2008-10-01 | Rolls Royce Plc | Blade arrangement |
GB0815475D0 (en) * | 2008-08-27 | 2008-10-01 | Rolls Royce Plc | A blade |
US8192102B2 (en) * | 2008-11-26 | 2012-06-05 | The Boeing Company | Load absorption system |
FR2970053B1 (en) * | 2011-01-05 | 2013-01-25 | Turbomeca | DEVICE AND METHOD FOR MECHANICAL PROTECTION |
US20130042630A1 (en) * | 2011-08-19 | 2013-02-21 | United Technologies Corporation | Gas turbine engine accessory mount |
US9109462B2 (en) * | 2011-12-15 | 2015-08-18 | United Technologies Corporation | Energy-absorbing fan case for a gas turbine engine |
US9982605B2 (en) | 2012-09-28 | 2018-05-29 | United Technologies Corporation | Auxiliary component mount including a fusible region configured to break at a predetermined load |
US9371835B2 (en) | 2013-07-19 | 2016-06-21 | Praxair Technology, Inc. | Coupling for directly driven compressor |
US10190439B2 (en) | 2014-04-23 | 2019-01-29 | Pratt & Whitney Canada Corp. | Frangible mounting arrangement and method for providing same |
FR3029996B1 (en) * | 2014-12-15 | 2018-05-04 | Safran Helicopter Engines | TORSIONALLY FRANGIBLE MECHANICAL FUSE AND COOLING UNIT OF A TURBOMOTER EQUIPPED WITH SUCH A FUSE |
GB2537613B (en) * | 2015-04-20 | 2019-05-22 | Rolls Royce Plc | A shaft assembly comprising a frangible coupling and a flexible coupling |
GB201611524D0 (en) | 2016-07-01 | 2016-08-17 | Rolls Royce Plc | Rotor blade damage |
EP3296540B1 (en) | 2016-09-20 | 2019-01-23 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
EP3296525B1 (en) * | 2016-09-20 | 2019-11-27 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine with a geared turbofan arrangement |
FR3063313B1 (en) | 2017-02-28 | 2022-10-28 | Safran Aircraft Engines | AIRCRAFT ENGINE INPUT ARRANGEMENT INCLUDING A MECHANICAL DECOUPLER |
GB201704045D0 (en) * | 2017-03-14 | 2017-04-26 | Rolls Royce Plc | A seal panel for gas turbine engine |
US11332236B2 (en) * | 2017-05-27 | 2022-05-17 | Borealis Technical Limited | Force limiting system and method for limiting loads in a powered aircraft landing gear drive wheel |
US10837320B2 (en) * | 2018-09-25 | 2020-11-17 | Honeywell International Inc. | Frangible strut for gas turbine engine |
US11499447B2 (en) * | 2020-01-15 | 2022-11-15 | Pratt & Whitney Canada Corp. | Bearing support with frangible tabs |
US11352979B2 (en) | 2020-04-24 | 2022-06-07 | Raytheon Technologies Corporation | Housing less front bearing compartment for gas turbine engine |
US11668316B1 (en) * | 2022-01-07 | 2023-06-06 | Hamilton Sundstrand Corporation | Rotor formed of multiple metals |
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EP1199441A2 (en) * | 2000-10-20 | 2002-04-24 | General Electric Company | Frangible coupling ring for a fan rotor |
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EP1314858A2 (en) * | 2001-11-23 | 2003-05-28 | MTU Aero Engines GmbH | Frangible bearing support for a turbomachine rotor |
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US4086012A (en) * | 1976-09-20 | 1978-04-25 | The United States Of America As Represented By The Secretary Of The Navy | Rotational energy absorbing coupling |
GB2079402B (en) * | 1980-06-27 | 1984-02-22 | Rolls Royce | System for supporting a rotor in conditions of dynamic imbalance |
FR2752024B1 (en) * | 1996-08-01 | 1998-09-04 | Snecma | SHAFT SUPPORT BREAKING AT THE APPEARANCE OF A BALOURD |
JPH10259830A (en) * | 1997-03-21 | 1998-09-29 | Toyota Autom Loom Works Ltd | Power transmission structure |
GB2323637B (en) * | 1997-03-25 | 2000-12-13 | Rolls Royce Plc | Ducted fan gas turbine engine |
-
2002
- 2002-07-12 GB GBGB0216312.9A patent/GB0216312D0/en not_active Ceased
-
2003
- 2003-06-12 GB GB0313659A patent/GB2391267B/en not_active Expired - Fee Related
- 2003-06-13 EP EP03253772A patent/EP1382805B1/en not_active Expired - Fee Related
- 2003-06-13 DE DE60306853T patent/DE60306853T2/en not_active Expired - Lifetime
- 2003-06-23 US US10/600,443 patent/US7025560B2/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB928250A (en) * | 1962-01-12 | 1963-06-12 | Rolls Royce | Bearing |
EP1199441A2 (en) * | 2000-10-20 | 2002-04-24 | General Electric Company | Frangible coupling ring for a fan rotor |
US6428269B1 (en) * | 2001-04-18 | 2002-08-06 | United Technologies Corporation | Turbine engine bearing support |
EP1314858A2 (en) * | 2001-11-23 | 2003-05-28 | MTU Aero Engines GmbH | Frangible bearing support for a turbomachine rotor |
Also Published As
Publication number | Publication date |
---|---|
EP1382805B1 (en) | 2006-07-19 |
US7025560B2 (en) | 2006-04-11 |
DE60306853D1 (en) | 2006-08-31 |
EP1382805A3 (en) | 2004-11-10 |
EP1382805A2 (en) | 2004-01-21 |
GB0216312D0 (en) | 2002-08-21 |
DE60306853T2 (en) | 2007-02-15 |
GB2391267B (en) | 2005-02-16 |
GB0313659D0 (en) | 2003-07-16 |
US20040006967A1 (en) | 2004-01-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20200612 |