EP2896794B1 - Blisk - Google Patents
Blisk Download PDFInfo
- Publication number
- EP2896794B1 EP2896794B1 EP15150251.5A EP15150251A EP2896794B1 EP 2896794 B1 EP2896794 B1 EP 2896794B1 EP 15150251 A EP15150251 A EP 15150251A EP 2896794 B1 EP2896794 B1 EP 2896794B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blisk
- lid
- blades
- filler
- disk part
- 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.)
- Not-in-force
Links
- 239000000945 filler Substances 0.000 claims description 47
- 230000015572 biosynthetic process Effects 0.000 claims description 19
- 238000005755 formation reaction Methods 0.000 claims description 19
- 238000013016 damping Methods 0.000 claims description 16
- 230000014759 maintenance of location Effects 0.000 claims description 16
- 239000002131 composite material Substances 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- GQWNECFJGBQMBO-UHFFFAOYSA-N Molindone hydrochloride Chemical compound Cl.O=C1C=2C(CC)=C(C)NC=2CCC1CN1CCOCC1 GQWNECFJGBQMBO-UHFFFAOYSA-N 0.000 claims description 2
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 2
- 230000001141 propulsive effect Effects 0.000 description 6
- 239000000806 elastomer Substances 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Images
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
Definitions
- the present invention relates to a blisk for a gas turbine engine.
- a blisk is a component having a rotor disk part and integral blades.
- An outer surface or rim of the disk part generally forms the inner working gas annulus of the engine.
- blisks are configured to avoid, where possible, forced responses from resonance and flutter.
- blisks lack inherent damping when compared to conventional bladed disk assemblies, and forced responses to resonances and flutter cannot always be avoided.
- fixing the inner working gas annulus at the outer surface of the disk part also fixes the basic size and shape of the disk part, and thus reduces options for reconfiguring the blisk to avoid forced responses and flutter.
- EP0077039 relates to a mixed flow cooling fan for an automotive internal combustion engine.
- EP2332765 and US2011/030336 relate to blisks for gas turbine engines.
- GB2463036 relates to a blisk for a gas turbine engine, the blades of the blisk have platforms and insert elements are provided between the platforms.
- An aim of the present invention is to provide an improved blisk which is, for example, less susceptible to forced responses and flutter.
- the present invention provides a blisk a for a gas turbine engine according to claim 1.
- the annulus fillers rather than an outer surface or rim of the disk part, can thus form the inner working gas annulus of the engine.
- the radius of the disk part can be reduced and the length of the blades increased.
- Reducing the radius of the disk part can also allow the total weight of the blisk to be decreased.
- annulus fillers can themselves act as damper elements between the blades, reducing blade resonances by physical contact with the blades.
- the present invention provides a gas turbine engine, such as aeroengine, having the blisk of the first aspect.
- the blisk may be a fan blisk or a compressor section blisk.
- each blade may continue radially inwardly of the respective lines of contact such that if the lids are moved radially inwardly, all the regions of suction and pressure side surfaces of the blades thereby revealed radially outwardly of the lids are aerofoil surface regions.
- Damping strips which extend along the opposite edges of the lid to contact the suction and pressure sides of the adjacent blades can help to improve the damping properties of the fillers.
- the strips may be formed of elastomer.
- the strips can be adhesively bonded to the lid.
- the annulus fillers may provide frictional damping. For example, rubbing along the contact lines between the lids and the blades can provide frictional damping.
- each annulus filler can be formed of a laminate a portion of whose lamina are elastomeric (the other portion can be e.g. metallic).
- each annulus filler may provide beneath the lid one or more retention formations which each retains a respective hook formed at the outer surface of the disk part and thereby holds the filler in position between its adjacent blades under centrifugal loading.
- the support structure can provide forward and rearward retention formations which respectively retain forward and rearward hooks formed at the outer surface of the disk part.
- the retention formations and hooks may be formed such that, on build, the annulus filler can be slid axially into position between its adjacent blades to mate the hooks with the retention formations.
- Damping pads e.g. formed of elastomer
- the pads can be adhesively bonded to the retention formations.
- the retention formations can be variously shaped. For example, they can be complimentary hooks to the disk part hooks.
- the complimentary hooks can be at the ends of respective legs (provided by the support structure) extending radially inwardly from the underside of the lid.
- Another option is for the retention formations to be straps which locate under the disk part hooks. The straps can extend between side walls (provided by the support structure) extending radially inwardly from the opposite edges of the lid.
- each annulus filler may provide a front and/or rear engagement formation at the front and/or rear end of the lid, the engagement formation engaging with a respective engine component (such as an adjacent fairing) to axially hold the filler in position between its adjacent blades.
- a respective engine component such as an adjacent fairing
- the annulus filler may be formed from aluminium alloy, titanium alloy, composite material (such as carbon fibre reinforced plastic) or a combination thereof.
- such materials are relatively lightweight, helping to reduce the weight of the blisk.
- a lightweight filler will tend to be less damaging to the engine.
- the blades may be welded (e.g. linear friction welded) to the disk part.
- welded e.g. linear friction welded
- a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X.
- the engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, an intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19.
- a nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
- air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust.
- the intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
- the compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
- the resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
- the high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
- a blisk may be used to form the propulsive fan 12 or may be part of a compressor section 13, 14 of such an engine.
- Figure 2 shows a close-up view of a blisk propulsive fan 12.
- the blisk has a rotor disk part 30 and a circumferential row of fan blades 32.
- Annulus fillers 34 shown in more detail in Figures 3 to 5 , bridge the gaps between adjacent blades.
- Each annulus filler 34 has an outer lid 36 which forms the inner surface of the working gas annulus of the engine, and an inner support structure which connects to the disk part 30 to support the lid on the blisk 12. Opposite edges of the lid respectively contact the suction side aerofoil surface of one blade and the pressure side aerofoil surface of an adjacent blade along contact lines 38.
- the annulus fillers 34 provide a number of advantages. They provide damping to the blades 32 by physical contact. This reduces aerofoil vibration from forced response and flutter, and thus improves the service life.
- the fillers also offer more flexibility in the blisk design, allowing the outer rim of the disk part 30 of the blisk to be reduced in diameter. The overall weight of the blisk 12 may thus be reduced for a given application, as the diameter of the disc part is reduced. Further, the natural frequency of the blades can be reduced due to the increase in blade length. This can be of particular benefit if there is a need to reduce the frequency of the fundamental flap mode/first engine order resonance. For example, there may be a need to keep the fundamental flap mode/first engine order resonance below a particular engine speed to reduce the forcing level.
- the aerofoil surfaces of the blade 32 continue uninterruptedly below the level of the lids 36. This allows design changes to be made to the engine whereby new annulus fillers can be installed whose lids have differently shaped air-washed surfaces.
- Each annulus filler 34 is assembled between and interfaces with adjacent blades 32 on the blisk 12, thus effectively forming an annular ring out of the lids 36.
- the ring covers the regions where the join welds (which may be linear friction welds) between the blades 32 and the disk part 30 are typically made, thereby making weld surface finish in these regions a less critical aerodynamic issue.
- FIG. 3 shows front and rear hooks 40 machined integrally to the outer surface of the disk part 30.
- the hooks can alternatively be welded to the disk part. They can be located spatially on the disk part to suit the particular intended application, e.g. they can be located closer to the leading and trailing edges of the disk part than shown.
- the support structure of each filler comprises retention formations in the form of corresponding hooks 42 at the ends of respective legs 44 extending from the underside of the filler's lid. On build, the filler is slid axially into position between its adjacent blades so that the hooks 40, 42 mate with each other and provide radial retention of the fillers under centrifugal loading.
- the filler's support structure can provide other configurations for the retention formations, such as straps running between side walls extending from the opposite edges of the filler, the straps locating in use underneath the hooks 40.
- Axial retention of the annulus fillers 34 can be achieved by fixing an engagement formation 46 at the front of each filler to the disk part 30 or to a suitable adjacent fairing such as the engine nose cone 50.
- Other filler configurations may adopt a single hook 42 with positive front and rear engagement of the filler.
- the annulus filler is constructed of light alloy or composite material, such as aluminium, titanium, carbon fibre composite or a mixture of these materials.
- Damping strips 48 can extend along the opposite edges of each lid 36 for contact with the adjacent blades 32.
- the strips can be formed, for example, of elastomer, which may be adhesively bonded to the lid.
- the strips are pre-formed to conform to the shape of the contacting aerofoil surfaces. Instead of such strips, however, frictional damping at the interfaces between the lids and the blades can be used.
- damping pads at the interfaces between the mating hooks 40, 42.
- Such pads can also be formed of elastomer and may be adhesively bonded to the filler hooks 42.
- the legs of the annulus damper can be constructed in such a manner as to be flexible, e.g. as a laminate formed layers of metal and elastomer, so as to provide additional damping.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
- The present invention relates to a blisk for a gas turbine engine.
- A blisk is a component having a rotor disk part and integral blades. By making the blades integral with the disk part, the need to attach the blades to a rotor disk is eliminated. Improvements in efficiency can thereby be obtained. Additionally, sources of crack initiation can be eliminated.
- An outer surface or rim of the disk part generally forms the inner working gas annulus of the engine.
- Typically blisks are configured to avoid, where possible, forced responses from resonance and flutter. However, blisks lack inherent damping when compared to conventional bladed disk assemblies, and forced responses to resonances and flutter cannot always be avoided. Further, fixing the inner working gas annulus at the outer surface of the disk part also fixes the basic size and shape of the disk part, and thus reduces options for reconfiguring the blisk to avoid forced responses and flutter.
-
EP0077039 relates to a mixed flow cooling fan for an automotive internal combustion engine.EP2332765 andUS2011/030336 relate to blisks for gas turbine engines.GB2463036 - An aim of the present invention is to provide an improved blisk which is, for example, less susceptible to forced responses and flutter.
- In a first aspect, the present invention provides a blisk a for a gas turbine engine according to claim 1.
- In contrast to conventional blisks, the annulus fillers, rather than an outer surface or rim of the disk part, can thus form the inner working gas annulus of the engine. In this way, the radius of the disk part can be reduced and the length of the blades increased. These changes allow the natural frequency of the blades to be reduced. This can be advantageous if, for example, there is a need to keep the fundamental flap mode/first engine order resonance below a particular engine speed to reduce the forcing level.
- Reducing the radius of the disk part can also allow the total weight of the blisk to be decreased.
- Further, the annulus fillers can themselves act as damper elements between the blades, reducing blade resonances by physical contact with the blades.
- In a second aspect, the present invention provides a gas turbine engine, such as aeroengine, having the blisk of the first aspect. In particular, the blisk may be a fan blisk or a compressor section blisk.
- Optional features of the invention will now be set out. These are applicable singly or in any combination with any aspect of the invention.
- The suction side and pressure side aerofoil surfaces of each blade may continue radially inwardly of the respective lines of contact such that if the lids are moved radially inwardly, all the regions of suction and pressure side surfaces of the blades thereby revealed radially outwardly of the lids are aerofoil surface regions. By effectively continuing the blades as aerofoil bodies radially inwards of the lids (even though below the lids the blades are not in the working gas annulus), the increased weight of the blades due to their increased length can be reduced. An alternative of e.g. introducing a (suitably mechanically stable) step-change in the blade cross-sectional shape at the contact line would tend to add more weight to the blisk. The continuance of the blades as aerofoil bodies below the lids also allows the annulus fillers to be replaced by new fillers having lids with different aerodynamic profiles even if these different profiles lead to exposure of more blade surface above the level of the lids.
- Damping strips which extend along the opposite edges of the lid to contact the suction and pressure sides of the adjacent blades can help to improve the damping properties of the fillers. The strips may be formed of elastomer. The strips can be adhesively bonded to the lid.
- Additionally, or alternatively, the annulus fillers may provide frictional damping. For example, rubbing along the contact lines between the lids and the blades can provide frictional damping.
- Another source of damping can be internal to the material of the support structure. For example, some or all of the support structure of each annulus filler can be formed of a laminate a portion of whose lamina are elastomeric (the other portion can be e.g. metallic).
- The support structure of each annulus filler may provide beneath the lid one or more retention formations which each retains a respective hook formed at the outer surface of the disk part and thereby holds the filler in position between its adjacent blades under centrifugal loading. For example, the support structure can provide forward and rearward retention formations which respectively retain forward and rearward hooks formed at the outer surface of the disk part. Conveniently, the retention formations and hooks may be formed such that, on build, the annulus filler can be slid axially into position between its adjacent blades to mate the hooks with the retention formations. Damping pads (e.g. formed of elastomer) may be located at the interfaces between the retention formations and hooks. Such pads can help to improve the damping properties of the filler. The pads can be adhesively bonded to the retention formations.
- The retention formations can be variously shaped. For example, they can be complimentary hooks to the disk part hooks. The complimentary hooks can be at the ends of respective legs (provided by the support structure) extending radially inwardly from the underside of the lid. Another option is for the retention formations to be straps which locate under the disk part hooks. The straps can extend between side walls (provided by the support structure) extending radially inwardly from the opposite edges of the lid.
- The support structure of each annulus filler may provide a front and/or rear engagement formation at the front and/or rear end of the lid, the engagement formation engaging with a respective engine component (such as an adjacent fairing) to axially hold the filler in position between its adjacent blades.
- The annulus filler may be formed from aluminium alloy, titanium alloy, composite material (such as carbon fibre reinforced plastic) or a combination thereof. Advantageously, such materials are relatively lightweight, helping to reduce the weight of the blisk. In addition, in the event of accidental filler release, a lightweight filler will tend to be less damaging to the engine.
- The blades may be welded (e.g. linear friction welded) to the disk part. When the annulus fillers cover the weld joins, these become aerodynamically less critical, whereby it is less important to maintain a high quality of surface finish in these regions.
- Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:
-
Figure 1 shows a longitudinal cross-section through a ducted fan gas turbine engine; -
Figure 2 shows a close-up, longitudinal cross-section view of a blisk propulsive fan; -
Figure 3 shows a close-up, longitudinal cross-section view of an annulus filler of the blisk of -
Figure 2 ; -
Figure 4 shows a perspective view of the lid of an annulus filler and two adjacent blades of the blisk ofFigure 2 ; and -
Figure 5 shows a perspective view an annulus filler of the blisk ofFigure 2 . - With reference to
Figure 1 , a ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and has a principal and rotational axis X-X. The engine comprises, in axial flow series, an air intake 11, apropulsive fan 12, anintermediate pressure compressor 13, a high-pressure compressor 14,combustion equipment 15, a high-pressure turbine 16, anintermediate pressure turbine 17, a low-pressure turbine 18 and a coreengine exhaust nozzle 19. Anacelle 21 generally surrounds theengine 10 and defines the intake 11, abypass duct 22 and abypass exhaust nozzle 23. - During operation, air entering the intake 11 is accelerated by the
fan 12 to produce two air flows: a first air flow A into theintermediate pressure compressor 13 and a second air flow B which passes through thebypass duct 22 to provide propulsive thrust. Theintermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to thehigh pressure compressor 14 where further compression takes place. - The compressed air exhausted from the high-
pressure compressor 14 is directed into thecombustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high andintermediate pressure compressors fan 12 by suitable interconnecting shafts. - A blisk may be used to form the
propulsive fan 12 or may be part of acompressor section Figure 2 shows a close-up view of a bliskpropulsive fan 12. The blisk has arotor disk part 30 and a circumferential row offan blades 32.Annulus fillers 34, shown in more detail inFigures 3 to 5 , bridge the gaps between adjacent blades. - Each
annulus filler 34 has anouter lid 36 which forms the inner surface of the working gas annulus of the engine, and an inner support structure which connects to thedisk part 30 to support the lid on theblisk 12. Opposite edges of the lid respectively contact the suction side aerofoil surface of one blade and the pressure side aerofoil surface of an adjacent blade along contact lines 38. - The
annulus fillers 34 provide a number of advantages. They provide damping to theblades 32 by physical contact. This reduces aerofoil vibration from forced response and flutter, and thus improves the service life. The fillers also offer more flexibility in the blisk design, allowing the outer rim of thedisk part 30 of the blisk to be reduced in diameter. The overall weight of theblisk 12 may thus be reduced for a given application, as the diameter of the disc part is reduced. Further, the natural frequency of the blades can be reduced due to the increase in blade length. This can be of particular benefit if there is a need to reduce the frequency of the fundamental flap mode/first engine order resonance. For example, there may be a need to keep the fundamental flap mode/first engine order resonance below a particular engine speed to reduce the forcing level. - Preferably, the aerofoil surfaces of the
blade 32 continue uninterruptedly below the level of thelids 36. This allows design changes to be made to the engine whereby new annulus fillers can be installed whose lids have differently shaped air-washed surfaces. - Each
annulus filler 34 is assembled between and interfaces withadjacent blades 32 on theblisk 12, thus effectively forming an annular ring out of thelids 36. The ring covers the regions where the join welds (which may be linear friction welds) between theblades 32 and thedisk part 30 are typically made, thereby making weld surface finish in these regions a less critical aerodynamic issue. -
Figure 3 shows front andrear hooks 40 machined integrally to the outer surface of thedisk part 30. The hooks can alternatively be welded to the disk part. They can be located spatially on the disk part to suit the particular intended application, e.g. they can be located closer to the leading and trailing edges of the disk part than shown. The support structure of each filler comprises retention formations in the form ofcorresponding hooks 42 at the ends ofrespective legs 44 extending from the underside of the filler's lid. On build, the filler is slid axially into position between its adjacent blades so that thehooks hooks 40. - Axial retention of the
annulus fillers 34 can be achieved by fixing anengagement formation 46 at the front of each filler to thedisk part 30 or to a suitable adjacent fairing such as theengine nose cone 50. Other filler configurations may adopt asingle hook 42 with positive front and rear engagement of the filler. - Typically, the annulus filler is constructed of light alloy or composite material, such as aluminium, titanium, carbon fibre composite or a mixture of these materials.
- Damping strips 48 can extend along the opposite edges of each
lid 36 for contact with theadjacent blades 32. The strips can be formed, for example, of elastomer, which may be adhesively bonded to the lid. Preferably the strips are pre-formed to conform to the shape of the contacting aerofoil surfaces. Instead of such strips, however, frictional damping at the interfaces between the lids and the blades can be used. - Further damping can be provided by providing damping pads at the interfaces between the mating hooks 40, 42. Such pads can also be formed of elastomer and may be adhesively bonded to the filler hooks 42. Similarly, the legs of the annulus damper can be constructed in such a manner as to be flexible, e.g. as a laminate formed layers of metal and elastomer, so as to provide additional damping.
- While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the scope of the invention as defined in the claims.
Claims (9)
- A blisk (12) for a gas turbine engine, the blisk having a rotor disk part (30), a circumferential row of blades (32) extending from and integral with the disk part, and the blisk further comprises a plurality of annulus fillers (34) bridging the gaps between adjacent blades; wherein each annulus filler has an outer lid (36) which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and an inner support structure which connects to the disk part to support the lid on the blisk, opposite edges of the lid making respective lines of contact (38) with a suction side aerofoil surface of one blade and a pressure side aerofoil surface of an adjacent blades, characterised in that the lid of each annulus filler has damping strips (48) which extend along the opposite edges of the lid to contact the suction and pressure sides of the adjacent blades..
- A blisk according to claim 1, wherein the suction side and pressure side aerofoil surfaces of each blade continue radially inwardly of the respective lines of contact such that if the lids are moved radially inwardly, all the regions of suction and pressure side surfaces of the blades thereby revealed radially outwardly of the lids are aerofoil surface regions.
- A blisk according to any one of the previous claims, wherein the support structure of each annulus filler provides beneath the lid one or more retention formations which each retains a respective hook (40) formed at the outer surface of the disk part and thereby holds the filler in position between its adjacent blades under centrifugal loading.
- A blisk according to claim 3, wherein the retention formations and hooks are formed such that, on build, the annulus filler can be slid axially into position between its adjacent blades to mate the hooks with the retention formations.
- A blisk according to any one of claim 3 or 4, wherein damping pads are located at the interfaces between the retention formations and hooks.
- A blisk according to any one of the previous claims, wherein the support structure of each annulus filler provides a front and/or rear engagement formation (46) at the front and/or rear end of the lid, the engagement formation engaging with a respective engine component (50) to axially hold the filler in position between its adjacent blades.
- A blisk according to any one of the previous claims, wherein the annulus filler is formed from aluminium alloy, titanium alloy, composite material or a combination thereof.
- A blisk according to any one of the previous claims, wherein the blades are welded to the disk part.
- A gas turbine engine having the blisk of any one of the previous claims.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB201400756A GB201400756D0 (en) | 2014-01-16 | 2014-01-16 | Blisk |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2896794A1 EP2896794A1 (en) | 2015-07-22 |
EP2896794B1 true EP2896794B1 (en) | 2017-03-15 |
Family
ID=50239060
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15150251.5A Not-in-force EP2896794B1 (en) | 2014-01-16 | 2015-01-07 | Blisk |
Country Status (3)
Country | Link |
---|---|
US (1) | US20150198174A1 (en) |
EP (1) | EP2896794B1 (en) |
GB (1) | GB201400756D0 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017530290A (en) * | 2014-08-22 | 2017-10-12 | シーメンス エナジー インコーポレイテッド | Modular turbine blade with separate platform support system |
US10294965B2 (en) | 2016-05-25 | 2019-05-21 | Honeywell International Inc. | Compression system for a turbine engine |
US10746031B2 (en) * | 2017-07-18 | 2020-08-18 | Rolls-Royce Corporation | Annulus filler |
US10670037B2 (en) * | 2017-11-21 | 2020-06-02 | General Electric Company | Turbofan engine's fan blade and setting method thereof |
US11078839B2 (en) | 2018-01-22 | 2021-08-03 | Rolls-Royce Corporation | Composite nosecone |
US11421538B2 (en) | 2020-05-12 | 2022-08-23 | Rolls-Royce Corporation | Composite aerofoils |
US11506083B2 (en) | 2020-06-03 | 2022-11-22 | Rolls-Royce Corporalion | Composite liners for turbofan engines |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5865999A (en) * | 1981-10-12 | 1983-04-19 | Nissan Motor Co Ltd | Slant flow type fan |
GB2251897B (en) * | 1991-01-15 | 1994-11-30 | Rolls Royce Plc | A rotor |
US6354780B1 (en) * | 2000-09-15 | 2002-03-12 | General Electric Company | Eccentric balanced blisk |
US7278821B1 (en) * | 2004-11-04 | 2007-10-09 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
GB0611031D0 (en) * | 2006-06-06 | 2006-07-12 | Rolls Royce Plc | An aerofoil stage and a seal for use therein |
GB2463036B (en) * | 2008-08-29 | 2011-04-20 | Rolls Royce Plc | A blade arrangement |
US8667774B2 (en) * | 2009-08-05 | 2014-03-11 | The Boeing Company | Coannular ducted fan |
GB0919657D0 (en) * | 2009-11-11 | 2009-12-23 | Rolls Royce Plc | Annulus filler for a gas turbine engine |
GB201020857D0 (en) * | 2010-12-09 | 2011-01-26 | Rolls Royce Plc | Annulus filler |
-
2014
- 2014-01-16 GB GB201400756A patent/GB201400756D0/en not_active Ceased
-
2015
- 2015-01-07 US US14/591,432 patent/US20150198174A1/en not_active Abandoned
- 2015-01-07 EP EP15150251.5A patent/EP2896794B1/en not_active Not-in-force
Also Published As
Publication number | Publication date |
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EP2896794A1 (en) | 2015-07-22 |
US20150198174A1 (en) | 2015-07-16 |
GB201400756D0 (en) | 2014-03-05 |
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