US20150118036A1 - Fan case for aircraft engine - Google Patents
Fan case for aircraft engine Download PDFInfo
- Publication number
- US20150118036A1 US20150118036A1 US14/563,527 US201414563527A US2015118036A1 US 20150118036 A1 US20150118036 A1 US 20150118036A1 US 201414563527 A US201414563527 A US 201414563527A US 2015118036 A1 US2015118036 A1 US 2015118036A1
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- US
- United States
- Prior art keywords
- fan
- case
- case body
- resin
- containment section
- 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.)
- Abandoned
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Classifications
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- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
- F04D19/002—Axial flow fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/615—Filler
-
- 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
Definitions
- FIG. 8 shows characteristics of absorbed energy at the containment section in the Example.
- the shear area P1 is small, and the delamination area P2 is large. That is, in the containment section 22 , since the bonding force among the fibers 23 B is weak, the fibers 23 B can flexibly move. Thus, in association with decrease of the shear force applied on the fibers 23 B, the proportion of the fibers 23 B that rupture due to tension increases, and as a result, the delamination area P2 increases.
- the fiber 23 B below is laid in one direction, and then, the fiber 23 B is laid thereon in a direction perpendicular thereto. This laying process is repeated desired times. Then, so laid fibers 23 are sewn together with a polyester thread to obtain an intermediate fiber layer 28 B. Then, as shown in FIG. 7B , the intermediate fiber layers 28 B are each interposed between the prepregs 28 A which are the same as those employed in the case body 21 . Each intermediate fiber layer 28 B is composed of fibers not impregnated with resin. Therefore, the containment section 22 including the intermediate fiber layers 28 B contains a less amount of the resin and a larger amount of the fiber as a whole, than the case body 21 composed only of the prepregs.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An annular fan case which covers an outer periphery of a fan in an aircraft engine includes: a case body including a first composite material containing a fiber and a resin; and a containment section including a second composite material containing a fiber and a resin, the containment section being formed on an outer periphery of the case body. A resin content of the containment section is set to be lower than the resin content of the case body.
Description
- CROSS REFERENCE TO THE RELATED APPLICATION
- This application is a continuation application, under 35 U.S.C. §111(a), of international application No. PCT/JP2013/066295, filed Jun. 13, 2013, which claims priority to Japanese patent application No. 2012-139484, filed Jun. 21, 2012, the disclosure of which are incorporated by reference in their entirety into this application.
- 1. Field of the Invention
- The present invention relates to a fan case which covers the outer periphery of a fan in an aircraft engine.
- 2. Description of Related Art
- In an aircraft engine, the weight thereof greatly affects the fuel consumption performance of an aircraft, and thus, weight reduction of the aircraft engine has been an important issue. In particular, in turbofan engines and turbojet engines, various attempts have been made to reduce the weight of the fan case being a component that accounts for a relatively large proportion in weight, and as a result, certain improvement has been attained. Representatives of such improved fan cases are those using a raw material other than metal which has been conventionally used as a raw material in general. Examples of such fan cases include a CFRP fan case, a fan case including an aluminum case body having Kevlar (registered trademark) fibers wound therearound multiple times, and still further, a fan case including a case body whose outer periphery is covered with an elastic containment belt (see Patent Document 1).
- On the other hand, the fan case is required to have a containment function of, at occurrence of FBO (Fan Blade Off) which is an event that a portion of a large number of fan blades provided radially on the outer periphery of a hub in the fan is chipped off due to some cause and thrown away due to the centrifugal force, flexibly receiving thrown chips or fragments so as to prevent the fragments from penetrating through the fan case. Therefore, weight reduction of the fan case needs to be performed while the containment function is ensured.
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- [Patent Document 1] Japanese National Phase PCT Laid-Open Publication No. 2002-516945
- The metal fan case is a simple one manufactured by cutting a metal raw material, but it is difficult to achieve sufficient weight reduction while ensuring the containment function. The CFRP fan case is intended to realize weight reduction by using a composite material having greater specific strength than metal. Further, an aluminum/Kevlar fiber fan case is provided with a necessary rigidity as a case by the use of aluminum, and with a containment function by the use of Kevlar fibers. These CFRP fan case and aluminum/Kevlar fiber fan case can achieve a certain level of weight reduction compared with metal fan cases, but with these fan cases, it is difficult to realize further weight reduction while sufficiently ensuring the containment function. Moreover, with respect to the aluminum/Kevlar fiber fan case, the deformation amount of the fan case is large when FBO has occurred. Thus, the aluminum/Kevlar fiber fan case may cause interference with surrounding components such as a cowl on the outside. On the other hand, if the number of windings of Kevlar fiber is increased in order to reduce the deformation amount of the fan case, weight reduction cannot be attained.
- Therefore, an object of the present invention is to provide a fan case for an aircraft engine, which is able to realize sufficient weight reduction while ensuring required containment performance.
- In order to achieve the above object, a fan case for an aircraft engine according to the present invention is constituted to cover an outer periphery of a fan including fan blades, the fan case including: a case body including a first composite material containing a fiber and a resin; and a containment section including a second composite material containing a fiber and a resin, the containment section being formed on an outer periphery of the case body, wherein a resin content of the containment section is set to be lower than a resin content of the case body.
- Since the containment section has a lower resin content than the case body, the fiber bonding strength between fibers is rendered to be weak. Accordingly, the containment section has flexibility that allows fibers to be displaced relative to each other. When fibers are bonded together, breakage due to shear occurs, but when fibers are displaced relative to each other, breakage due to tension occurs. Therefore, in the containment section, among all fibers that are broken when fan blade fragments having flown away and collided therewith, the proportion of fibers that are broken due to tension increases, while the proportion of fibers that are broken due to shear decreases. In general, breakage due to tension requires more energy than breakage due to shear, and hence, the amount of energy that can be absorbed in the entirety of the containment section increases. In other words, the containment section has a high containment function that can prevent fan blade fragments from penetrating therethrough. Accordingly, the case body need not have a containment function. Thus, sufficient weight reduction of the case body can be attained while allowing the case body to have high strength and high rigidity that can realize assurance of a tip clearance relative to the tip portion of each fan blade, retainment of each stator vane, and the like.
- Preferably, the containment section is formed on an outer periphery of a portion of the case body which portion faces the fan blades from radially outside. Accordingly, the area where the containment section is formed can be reduced, and further weight reduction can be realized.
- The fibers in the respective first and second composite materials may be identical in composition, and the resins in the respective first and second composite materials may be identical in composition. Accordingly, the number of kinds of fiber and resin to be used is reduced, and thus, productivity can be increased.
- Preferably, the resin content of the containment section is 12 to 15% by weight. Preferably, the resin content of the case body is about 32 to 40% by weight. Accordingly, the containment function and the weight reduction can be realized in good balance.
- For example, the fiber forming the first or second composite material is a fiber selected from the group consisting of carbon fibers, glass fibers, and aramid fibers, and the resin, forming the first or second composite material is a resin selected from the group consisting of epoxy resins, phenol resins, bismaleimide resins and polyimide resins. With these materials, light and high strength composite materials can be obtained.
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FIG. 1 schematically shows the structure of an aircraft engine on which a fan case according to one embodiment of the present invention is mounted; -
FIG. 2 is a front view showing the aircraft engine; -
FIG. 3 is a longitudinal sectional view showing a fan and the fan case in the aircraft engine; -
FIG. 4A is a cross-sectional view schematically showing the internal structure of a case body of the fan case; -
FIG. 4B is a cross-sectional view schematically showing the internal structure of a containment section of the fan case; -
FIG. 5 is a schematic diagram showing the internal structure of the case body of the fan case when a fan blade fragments having been chipped off and thrown away has collided with the case body; -
FIG. 6 is a schematic diagram showing the internal structure of the containment section of the fan case when a fan blade piece having been chipped off and thrown away has collided with the containment section; -
FIG. 7A is a cross-sectional view schematically showing the internal structure of the case body of the fan case according to an Example of the present invention; -
FIG. 7B is a cross-sectional view schematically showing the internal structure of the containment section of the fan case according to an Example of the present invention; and -
FIG. 8 shows characteristics of absorbed energy at the containment section in the Example. - Hereinafter, a preferred embodiment of the present invention will be described with reference to the drawings. In
FIG. 1 , a jet engine E for an aircraft is a two-shaft turbofan engine, and includes acompressor 2, acombustor 3, a turbine 4, and afan 10, as main components. Compressed air supplied from thecompressor 2 is mixed with fuel and the mixture is combusted in thecombustor 3. Combustion gas of high temperature and high pressure generated as a result of the combustion is supplied to the turbine 4. The turbine 4 includes ahigh pressure turbine 41 on the former stage side and alow pressure turbine 42 on the latter stage side. Thecompressor 2 is connected to thehigh pressure turbine 41 via ahigh pressure shaft 7 which is hollow, and is driven to rotate by thehigh pressure turbine 41. - The
fan 10 is connected to thelow pressure turbine 42 via alow pressure shaft 9 inserted through the hollow portion of thehigh pressure shaft 7, and is driven to rotate by thelow pressure turbine 42. Thefan 10 is mounted to the front end of thelow pressure shaft 9, and is covered with a fan case FC. Thehigh pressure shaft 7 and thelow pressure shaft 9 are in concentric arrangement having a common engine shaft center C. By a jet flow of combustion gas ejected from thelow pressure turbine 42 and a high speed air flow generated by thefan 10, engine thrust is obtained. - As shown in
FIG. 2 , in thefan 10, a large number of fan blades (rotor vanes) 12 are radially provided along radial directions of the engine E, on the outer periphery of ahub 11 connected so as to integrally rotate with the low pressure shaft 9 (FIG. 1 ). Thefan 10 is housed in the fan case FC having an annular shape (cylindrical shape) which covers the outer periphery of thefan 10. In case when a portion offan blades 12 has been chipped off and thrown away, it is received within the fan case FC so as not to break out of the engine E. The entirety of the engine E including thefan 10 and the fan case FC is covered with an engine nacelle N. - As shown in
FIG. 3 , thefan 10 is provided withfan stator vanes 13 downstream of thefan blades 12. The fan case FC includes acase body 21 havingflanges containment section 22 mounted on the outer periphery surface of thecase body 21. Thecontainment section 22 is formed only on the outer periphery of a portion of thecase body 21 which portion faces thefan blades 12 from radially outside. The length in the axial direction of thecontainment section 22 is set to be greater than the axial length of atip portion 12 a of eachfan blade 12. Thecase body 21 is formed from a first composite material containing a fiber and a resin, and thecontainment section 22 is formed from a second composite material containing a fiber and a resin. In this embodiment, the first and second composite materials are formed from the same fiber and the same resin, but the resin content in the composite material for thecontainment section 22 is set to be lower than that of thecase body 21. - Composite materials, light in weight and of high strength, as the raw materials of the
case body 21 and thecontainment section 22, can preferably employ a carbon fiber, a glass fiber, an aramid fiber, or the like, as the fiber. As the resin which serves as a base material to be filled among a plurality of layers made of this fiber and to bond adjacent two fiber layers, a thermosetting resin such as an epoxy resin, a phenol resin, a bismaleimide resin, or a polyimide resin can be preferably used. In manufacturing, the composite material for forming thecase body 21 is laminated on a frame or mold for lamination, the composite material for forming thecontainment section 22 is laminated thereon, and then, both composite materials are heated to be cured. - The
case body 21 of the fan case FC is set to have an inner diameter that allows thecase body 21 to face, with a required small tip clearance TC, thetip portion 12 a of eachfan blade 12. In order to increase the engine efficiency, the inner peripheral surface of thecase body 21 is controlled with a high dimensional accuracy, and thecase body 21 is required to have strength and rigidity that can always ensure the required small tip clearance TC. Thus, thecase body 21 is formed of a high rigidity composite material that is hard and less likely to deform. That is, in this embodiment, the composite material for thecase body 21 employs a composite material that has been conventionally used in general, in which a resin is sufficiently contained among a plurality of fiber layers laminated in the radial direction, and the resin content is set to a value that realizes high strength and high rigidity. - Separately from the
case body 21, the fan case FC includes thecontainment section 22 on the outer periphery side of thecase body 21. As described later, thecontainment section 22 has a containment function of preventing fan blade segments that have been chipped off and thrown away at occurrence of FBO, from breaking out of the fan case FC. Therefore, thecase body 21 need not have the containment function, and thus, weight reduction of thecase body 21 can be performed while allowing strength and rigidity that can realize assurance of the required tip clearance TC, retainment of thestator vanes 13, and the like. Actually, the rigidity of thecase body 21 is higher than the rigidity of thecontainment section 22. - As schematically shown in
FIG. 4A , thecase body 21 in the fan case FC is set to have a normal resin content used in general that allows high strength and high rigidity. Aresin 24A is sufficiently filled between layers made of afiber 23A, and thefibers 23A of the respective layers are strongly bonded to each other. Thus, thefibers 23A are in a state where they are less likely to be separated (delaminated) from each other. - On the other hand, as schematically shown in
FIG. 4B , thecontainment section 22 in the fan case FC is set to have a resin content lower than the normal resin content of thecase body 21 as shown inFIG. 4B . Since the amount of aresin 24B functioning as a bonding material is small, theresin 24B is not sufficiently filled between layers made of afiber 23B. Accordingly, manynon-impregnated portions 27, such as bubbles, which are not impregnated with resin emerge. As a result, the fiber bonding strength which bonds thefibers 23B of the respective layers together is weak, and thefibers 23B are easy to separate (delaminate) from each other and to be displaced relative to each other. Thus, compared with thecase body 21, thecontainment section 22 has flexibility that allows thefibers 23B to be flexibly deflect. -
FIG. 5 andFIG. 6 schematically show deformation states of the internal structures of thecase body 21 and thecontainment section 22, in a case where fan blade fragments 120 has chipped off at occurrence of FBO, and collided with thecase body 21 and thecontainment section 22, respectively. InFIG. 5 , when the chipped fan blade fragments 120 has collided with thecase body 21, since thefibers 23A are less likely to delaminate from each other, a shear area P1 in the radial direction in which thefibers 23A rupture or break mainly due to a shear force is large, and a delamination area P2 in the radial direction in which thefibers 23A rupture or break mainly due to tension is small. - On the other hand, as shown in
FIG. 6 , when the chipped fan blade fragments 120 has collided with thecontainment section 22, since thefibers 23B are in a flexible state where they are easy to delaminate from each other, the shear area P1 is small, and the delamination area P2 is large. That is, in thecontainment section 22, since the bonding force among thefibers 23B is weak, thefibers 23B can flexibly move. Thus, in association with decrease of the shear force applied on thefibers 23B, the proportion of thefibers 23B that rupture due to tension increases, and as a result, the delamination area P2 increases. - In general, when the
fibers fiber containment section 22, thecase body 21 whose shear area P1 is larger than that of thecontainment section 22 can be structured as to allow the fan blade fragments 120 to penetrate therethrough, as shown inFIG. 5 . Accordingly, weight reduction of thecase body 21 can be realized while allowing required strength and required rigidity. On the other hand, in thecontainment section 22 having a larger proportion of the delamination area P2 than that of thecase body 21, the amount of shock absorption energy against the fan blade fragments 120 colliding therewith is large. Thus, as shown inFIG. 6 , thecontainment section 22 exhibits an excellent containment function of preventing the fan blade fragments 120 which has penetrated through thecase body 21 to advance into thecontainment section 22, from penetrating through thecontainment section 22. - As described above, the fan case FC shown in
FIG. 3 includes thecase body 21 which covers thefan 10, and thecontainment section 22 for the containment function, and thecontainment section 22 is provided with the containment function, simply by setting the resin content thereof to be lower than the resin content of thecase body 21 to improve the flexibility thereof. Accordingly, in a case where the fan case FC has the same weight as that of an existing fan case, the fan case FC has higher containment ability than the existing one. In a case where the fan case FC has containment ability equivalent to that of an existing fan case, the fan case FC can be made lighter in weight than the existing one. Further, since thecontainment section 22 is provided only on a portion of thecase body 21 which portion faces thefan blades 12 from radially outside, further weight reduction can be realized. In the embodiment, for thecase body 21 and thecontainment section 22, composite materials of a combination of the same raw materials which are identical in composition are used, and they are formed simply by changing the resin content. Accordingly, there is no need to prepare two kinds of composite materials and thus, productivity is rendered to be high. - Next, examples of the present invention will be described.
- (Example of the Case Body 21)
- As shown in
FIG. 7A , thecase body 21 is formed by laminating onlymultiple prepregs 28A each obtained by laying thefiber 23A shown below to form a layer and causing theresin 24A to be contained therein by a certain amount in advance. The resin content of theprepreg 28A is 35% by weight (hereinafter, may be expressed simply as “%”) substantially the same as that of a general prepreg. - The
fiber 23A=carbon fiber - The
resin 24A=epoxy resin - (Example of the Containment Section 22)
- The
fiber 23B below is laid in one direction, and then, thefiber 23B is laid thereon in a direction perpendicular thereto. This laying process is repeated desired times. Then, so laid fibers 23 are sewn together with a polyester thread to obtain anintermediate fiber layer 28B. Then, as shown inFIG. 7B , the intermediate fiber layers 28B are each interposed between theprepregs 28A which are the same as those employed in thecase body 21. Eachintermediate fiber layer 28B is composed of fibers not impregnated with resin. Therefore, thecontainment section 22 including the intermediate fiber layers 28B contains a less amount of the resin and a larger amount of the fiber as a whole, than thecase body 21 composed only of the prepregs. That is, the resin content in thecontainment section 22 is low. It should be noted that the resin contained in theprepregs 28A becomes fluid while being heat-cured, and spreads also inside the intermediate fiber layers 28B, whereby the distribution of the resin after the heat curing becomes almost uniform. Moreover, the polyester thread contained in theintermediate fiber layer 28B accounts for a very small proportion in weight and thus can be ignored. Thus, the resin content of thecontainment section 22 was set to 12%. - The
fiber 23B of theintermediate fiber layer 28B=carbon fiber -
FIG. 8 shows changes in absorbed energy vs changes in the resin content (% by weight) obtained through experiments when the surface density of thecontainment section 22 shown inFIG. 7B was set to 1.2 g/cm2. As seen fromFIG. 8 , with respect to thecontainment section 22, when the resin content is 15% or lower, the absorbed energy is greater, by 10% or higher, than the absorbed energy at theresin content 35%, which corresponds to a general composite material. When the resin content is lower than 12%, the bond between the resin and the fiber becomes weak, and the shape of the composite material cannot be maintained. Therefore, the resin content of thecontainment section 22 is preferably 12 to 15%. - In order to maintain high rigidity, the resin content of the
case body 21 is preferably about 32 to 40%, in particular around 35%. By using such composite materials as thecase body 21 and thecontainment section 22, the containment function and the weight reduction can be realized in good balance. - In the embodiment, an exemplary case has been shown in which the
case part 21 and thecontainment section 22 are formed from composite materials each being a combination of the same fiber and the same resin. However, the present invention is not limited thereto. Thecase body 21 and thecontainment section 22 may respectively employ composite materials in which at least one of the fiber and the resin is set to be different. - The present invention is not limited to the embodiment described above, and various additions, modifications, and deletions are possible without departing from the scope of the present invention. Such additions, modifications, and deletions are to be construed as included in the scope of the present invention.
- 10 fan
- 12 fan blade
- 21 case body
- 22 containment section
- 23A, 23B fiber
- 24A, 24B resin
- 28A prepreg
- 28B intermediate fiber layer
- 120 fan blade fragments
- FC fan case
Claims (7)
1. A fan case for an aircraft engine, for covering an outer periphery of a fan including fan blades, which comprises:
a case body including a first composite material containing a fiber and a resin; and
a containment section including a second composite material containing a fiber and a resin, the containment section being formed on an outer periphery of the case body, wherein
a resin content of the containment section is set to be lower than a resin content of the case body with non-impregnated portions formed in the containment section.
2. The fan case as claimed in claim 1 , wherein
the containment section is formed on an outer periphery of a portion of the case body which portion faces the fan blades from radially outside.
3. The fan case as claimed in claim 1 , wherein
the fibers in the respective first and second composite materials are identical in composition, and the resins in the respective first and second composite materials are identical in composition.
4. The fan case as claimed in claim 1 , wherein
the resin content of the containment section is 12 to 15% by weight.
5. The fan case as claimed in claim 4 , wherein
the resin content of the case body is 32 to 40% by weight.
6. The fan case as claimed in claim 1 , wherein
the fiber forming the first or second composite material is a fiber selected from a group of carbon fibers, glass fibers and aramid fibers.
7. The fan case as claimed in claim 1 , wherein
the resin forming the first or second composite material is a resin selected from a group of epoxy resins, phenol resins, bismaleimide resins, and polyimide resins.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012-139484 | 2012-06-21 | ||
JP2012139484 | 2012-06-21 | ||
PCT/JP2013/066295 WO2013191070A1 (en) | 2012-06-21 | 2013-06-13 | Fan case for aircraft engine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2013/066295 Continuation WO2013191070A1 (en) | 2012-06-21 | 2013-06-13 | Fan case for aircraft engine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20150118036A1 true US20150118036A1 (en) | 2015-04-30 |
Family
ID=49768667
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/563,527 Abandoned US20150118036A1 (en) | 2012-06-21 | 2014-12-08 | Fan case for aircraft engine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20150118036A1 (en) |
EP (1) | EP2865866A4 (en) |
JP (1) | JP5938474B2 (en) |
CN (1) | CN104334855B (en) |
CA (1) | CA2875928C (en) |
WO (1) | WO2013191070A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20190063460A1 (en) * | 2017-08-25 | 2019-02-28 | United Technologies Corporation | Fan containment case for gas turbine engines |
US10472985B2 (en) | 2016-12-12 | 2019-11-12 | Honeywell International Inc. | Engine case for fan blade out retention |
US20200180235A1 (en) * | 2018-12-05 | 2020-06-11 | United Technologies Corporation | High temperature composite seal |
CN112400052A (en) * | 2018-07-13 | 2021-02-23 | 劳斯莱斯股份有限公司 | Fan housing |
US11156126B2 (en) * | 2018-04-13 | 2021-10-26 | Raytheon Technologies Corporation | Fan case with interleaved layers |
EP3862266A4 (en) * | 2018-10-04 | 2021-12-01 | Honda Motor Co., Ltd. | Ducted fan device |
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US20140064938A1 (en) * | 2012-09-06 | 2014-03-06 | General Electric Company | Rub tolerant fan case |
CN107642504B (en) * | 2017-09-30 | 2019-08-23 | 中国航发沈阳发动机研究所 | The fancase of Screw assembly |
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Also Published As
Publication number | Publication date |
---|---|
CN104334855B (en) | 2016-12-14 |
JP5938474B2 (en) | 2016-06-22 |
EP2865866A1 (en) | 2015-04-29 |
WO2013191070A1 (en) | 2013-12-27 |
JPWO2013191070A1 (en) | 2016-05-26 |
EP2865866A4 (en) | 2016-03-23 |
CA2875928C (en) | 2017-01-17 |
CA2875928A1 (en) | 2013-12-27 |
CN104334855A (en) | 2015-02-04 |
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