CA2021087A1 - Ultra high bypass engine integrated fan/cowl and transportation/removal - Google Patents
Ultra high bypass engine integrated fan/cowl and transportation/removalInfo
- Publication number
- CA2021087A1 CA2021087A1 CA002021087A CA2021087A CA2021087A1 CA 2021087 A1 CA2021087 A1 CA 2021087A1 CA 002021087 A CA002021087 A CA 002021087A CA 2021087 A CA2021087 A CA 2021087A CA 2021087 A1 CA2021087 A1 CA 2021087A1
- Authority
- CA
- Canada
- Prior art keywords
- fan
- engine
- rotor
- module
- nacelle
- 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
Links
- 238000000034 method Methods 0.000 claims abstract description 23
- 238000000926 separation method Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 7
- 102000011781 Karyopherins Human genes 0.000 description 2
- 108010062228 Karyopherins Proteins 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 241000370685 Arge Species 0.000 description 1
- 241000606308 Engina Species 0.000 description 1
- 244000228957 Ferula foetida Species 0.000 description 1
- WJOHZNCJWYWUJD-IUGZLZTKSA-N Fluocinonide Chemical compound C1([C@@H](F)C2)=CC(=O)C=C[C@]1(C)[C@]1(F)[C@@H]2[C@@H]2C[C@H]3OC(C)(C)O[C@@]3(C(=O)COC(=O)C)[C@@]2(C)C[C@@H]1O WJOHZNCJWYWUJD-IUGZLZTKSA-N 0.000 description 1
- 102100034742 Rotatin Human genes 0.000 description 1
- 101710200213 Rotatin Proteins 0.000 description 1
- 244000269722 Thea sinensis Species 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007775 late Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229940052996 vanos Drugs 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
- B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
Abstract
ABSTRACT OF THE DISCLOSURE
Method and apparatus for enabling transport of very 1arge diameter gas turbine engines by seperating the engine into a stator module and a rotor module, the rotor module including all of the turbine and compressor stages of the engine. In one form, the transportable stator module includes an integrated fan case, fan cowl, and inlet. The stator module supports at least a forward portion of the rotor module with a plurality of circumferentially spaced structural outlet guide vanes. The vanes are detachable at the rotor module interface to enable removal of the rotor module from the stator module. The fan blades are separable from the rotor module to allow separation of the rotor ant stator modules.
Method and apparatus for enabling transport of very 1arge diameter gas turbine engines by seperating the engine into a stator module and a rotor module, the rotor module including all of the turbine and compressor stages of the engine. In one form, the transportable stator module includes an integrated fan case, fan cowl, and inlet. The stator module supports at least a forward portion of the rotor module with a plurality of circumferentially spaced structural outlet guide vanes. The vanes are detachable at the rotor module interface to enable removal of the rotor module from the stator module. The fan blades are separable from the rotor module to allow separation of the rotor ant stator modules.
Description
~2~ 7 ULTRA HIGH BYPASS ENG I NE INTEGRATED FAN/COUL
AN~ TRANSPORTATION/REMOVAL
BACKGROUND OF THE INVENTION
The present invention r~lates to a method and apparatus for assembly and mounting of a turbofan gas turbine engine and. more particularly. to integration of an engine fan casing with en8ine cowlinB and mounting arran~ement which permits disassembly of the core en8ine from the external fan assembly.
Turbofan gas turbine engines gencrally include a core en~ine coupled in driving relationship to a forward mounted fan module. The fan module, in a high-bypass ratio en~ine. includes a l~arge diam~ter sin~le stage fan and a multiple stage intermediate pressure compr~ssor or booster. The fa~ is surroundsd by a fan casing supported by a plurality of structural lS outlet guide vanes which are. in turn, support~d on a casing surrounding the booster. The core en8ine includes a hi8h pressure compressor, a combustor an~ a multi-stage turbine for extracting energy from combusticn gases exiting the combustor for triving the compressors and fan.
AN~ TRANSPORTATION/REMOVAL
BACKGROUND OF THE INVENTION
The present invention r~lates to a method and apparatus for assembly and mounting of a turbofan gas turbine engine and. more particularly. to integration of an engine fan casing with en8ine cowlinB and mounting arran~ement which permits disassembly of the core en8ine from the external fan assembly.
Turbofan gas turbine engines gencrally include a core en~ine coupled in driving relationship to a forward mounted fan module. The fan module, in a high-bypass ratio en~ine. includes a l~arge diam~ter sin~le stage fan and a multiple stage intermediate pressure compr~ssor or booster. The fa~ is surroundsd by a fan casing supported by a plurality of structural lS outlet guide vanes which are. in turn, support~d on a casing surrounding the booster. The core en8ine includes a hi8h pressure compressor, a combustor an~ a multi-stage turbine for extracting energy from combusticn gases exiting the combustor for triving the compressors and fan.
- 2 - 2~2~37 Mounting of such high-bypass engines on an aircraft generally requires one or more structural supports which connect the engine to a structural member. sometimes referred to as a strut or pylon, in a wing or fuselage, depending upon the mounting location. The structural supports extend throu~h an aerodynamic cowling, sometime- referred to as a nacelle, and couple to the en~ine casing. Coupling may be to the fan casing (or shroud) and to the casin~
surroundin~ the turbine. In general, some form of structural yoke is attached to the en~ine casing and the structural supports attach to the yoke.
As gas turbine en~ines have beccme more powerful and larger, a concern has develop0d with handlin~ ant lS transporting of such enginas. In particular, engines are now bein~ developed with fans and fan casings having diameters in the range of twelve feet.
Transporting of such engines b~ air or ground i~ not practical with current commercial aircraft and over the road transportation guidelines. Accordingly, it is desirable to provide a method of assembling such engines which permits transport without exceeding aircraft or ground transport size limitations.
The problems associated with handl ing and transporting of such large en~ines extends beyond shipments to the installation, removal, and handling of the ensines in aircraft s*rvicin~. It is therefore further desirable to provide a methot and apparatus for servicing of such engines which overcomes the problems associated with such large diameter fans.
~ 3 ~ 2~2~7 SUMMARY OF THE INVENTION
It is an object of the present invention to provide a method and apparatus for asssmbly and mounting of a hi~h-bypass ratio gas turbine en~ine which overcomes the above mentioned disadvantages of such engines.
It is another object of the present invention to provide a method and apparatus which permits separation of the fan and core en~ine plus boo~t~r without affectin~ acceptance testin8 of the ~ngin~.
It is yet another object of the present invention to provide a method and apparatus for incorporation of a fan shroud into an en8ine nacelle with structural support for the core en8ine derived from the nacelle.
The above and other objects. features and advantages are attained in one form in a high-bypass ratio ~as turbine en~ine in which the fan casing is incorporatet into an aircraft mounted cowling or nacslle and the fan casing is made separable from the core engine without disturbing ass~mbly of the intermediate stage or booster compressor. The nac~lle is modified to become a structural m~mber ant is structurally attached to at least one aircraft frame member or strut. Outlet ~uide vanos, normally couplin~ th~ fan shrout to the boo~ter casing. are connected between the nacelle and tho booster frame to support th~ en~ine within the nacelle. The connectir,3 supports are made separable from the booster casin~ to allow the cor~ enBine plus booster to be removable from the nacelle. Still further, the fan spinner and fan blades are made removable from the en~ine without disturbin~ the booster sta~e or removing the core engine. The entire core en~lne is thus intact and can l3DV-9908 ~ 4 - 2~0~7 be tested as a unit. Ths fan blades can be installed on the en~ine for testing purposes and removed for transporting. Such an arran8ement maintains the integrity of the assembled rotating components, e.~., S the compressor, turbine, booster and fan rotor, while allowing separation of elements which are either non-rotatin3 or do not require a rotating interface, such as, for example, the nacelle, outlet guide vanes and the fan blades. Although the fan blades rotate, their connection is a fixed attachment to the fan rotor and does not require a rotatirg interface.
In another form, the turbine en~ine may be characterized as comprisin~ a ~enerally cylindrical stator module transportable as a sin~le unit and includin8 an inte~rated fan casei fan cowl, and inlet.
The en~ine further comprises a rotor module transportable as a single unit and including a core en8ine with a rotatable fan rotor. The rotor module is removably attachable to the stator module. A
plurality of fan blades i5 removably at~achable to the fan rotor. The stator module may includa a plurality of circumferentially spaced and radially depending fan struts attached at one end along an inner surface of the stator module. Another end of the fan struts may 25 be removably attachable to the rotor module for supporting the rotor module within at least part of the stator module. At least some of th~ fan struts may project substantially perpendicular towart the centerline of the rotor module while others of the fan struts may comprise structural outlet guide vanes which project obliquely toward th0 centerlino of the rotor module. A spinner is desirably removably attached to the fan rotor forwart of the fan blades.
- 5 ~ 7 The invention may b0 further characterized as a method for assembling a turbo-fan en~ine having a rotor module including a core enBine with a rotatable fan rotor and furthsr having a stator module including an inte~rated fan casing. fan cowl and inlet. The method comprises removably attachin8 the rotor motule.
as a sinsle inte8rated unit. to the stator module ant thereafter attaching a plurality of fan blades to the fan rotor. The method may further comprise affixing a plurality of circumferentially spaced fan struts to the stator module with the fan struts extending generally radially from the stator module toward the rotor module and removably attachin~ inner ends of the fan struts to the rotor module for supporting the rotor module at least partially within the stator module.
BRIEF ~ E~ OF THE DRAWINGS
For a botter und~rstanding of the present invention. reference may be had to the following detailed description taken in conjunction with the accompanyin8 drawings in which:
FIG. 1 is a simplified partial cros~-sectional drawing of an exemplary gas turbine engine:
FIG. 2 is a ~implified drawin~ showin~ mounting cf the en8in~ of FIG. 1 on an aircraft win~:
FIC. 3 is a simplified drawing showing an en~ino arran8ement in accordance with the present invention mounted to an aircraft win~; and FIG. 4 i5 an exploded view of the en8ine arran8ement of FIG. 3 showing engine disa-~sembly.
- 6 - 2~21~3 1 DESCRIPTION OF THE PRFFERRED EM~ODIMENT
Referrin3 first to FIG. 1, there is shown a partial cross-sectional drawin~ of an exemplary high-bypass ratio gas turbine en8ine 10 having a core enBine portion indicated at 12 and a fan portion indicated at 14. The core en8ine or core engine portion 12 may be referred to as the rotor module while the fan portion 14 may be referred to as the stator module. In ~eneral, a_ least so~e ext nt of the rotor module lies within the stator module. The rotor module or core engine 12 includes an intermetiate pressure compressor or booster sta~e 16, a high pressure compressor stage 18. a combustor stage 20, a hiBh pressure turbine sta~e 21, and a low lS prsssure turbine stage 22 all aligned on an en8ine centerline 23. The fan portion 14 inclutes a plurality of fan blades 24. a fan shroud 26. a fan spinnsr 28 and a plurality of circumferentially spaced outlet guide vanes 30 which support the fan shroud 26.
The vanes 30 are attached to en8ine casing 32 adjacent the booster stage 16. The en~ine 10 aIso includes an aft core cowl 33 and a primary nozzl~ 35. A fan shaft 37 driv~n by turbine stage 22 extends throu~h the engine and is coupled in drivin~ relationship with booster stage 16 and fan blades 24 via a fan rotor 45.
The high pressure turbine stage 21 drives a compressor stage 18 through a hi~h pressure shaft 41.
As will be apparent from FIG. 1. handling of the engine 10 is a major problem for very largè diamater fan blates 24. While it is possible to remove the blades 24. the practice in the art is to treat the blades 24. booster sta~e 16, and casing 26 as a unitary module. Some engines are constructed with a ~ 7 ~ 2 ~ 210 8 7 two-piece fan shaft 37 separable aft of the boostsr sta~e 16 approximately along the line 43. These en8ines are identified as n sp 1 i t fan~ engines.
Assembly and/or disassembly of split fan engines is complicated since it is difficult to attach the fan forward shaft and the fan mid ~haft properly. In such fan split methods of separating an en~ine. the forward module or fan module includes the fan shroud 26, structural outlet guide vanes 30, fan spinner 28, fan rotor blades 24. alon~ with Ih0 fan rotor. booster sta~e 16 and the forward portion of shaft 37. Thus, it has not been practical to separate the fan module and large external components from the core en8ine to facilitate handlin~. Furthermore, it is not desirable to separate an engine where such separation includes a rotatin8 interface since such interface may involve bearings or critical alignments.
Turnin~ now to FIG. 2. there,is shown a simplified cross-sectional view of an en8ine similar to that of FIG. 1 mounted within an aerodynamic fan cowl 34 which is in turn coupled via a structural member 36 to an aircraft wing 33. The structural m~mber 38 and cowlin~ 34 are well known in the art and may be of the type shown. by way of example, in U.S. Patent No.
~5 4.132.069. Within the fan cowl 34, the member 36 is connected to the fan shroud 26. The shrout 26 is releasably connected to the cowl 34. The cowl 34 preferably includes an inlet section 37.
FIG. 3 illustrates an arranBement in accordance with the tea~hing of the present invention in a stylized repr~sontation of a turbofan en8ine. The fan cowl, indicated at, 40, is an inte~rated cowl incorporating the aerodynamic characteristics of the cowl 34 but incluting the structural features of a fan .
.
- 8 - 2~2~a~7 casin~. In partic~lar, the fan shrout 26 is now an integrated part of cowl 40 as shown by the increased thickness in the cross-sectional dimensions of FIG. 3.
The structural member 36 attaches to the cowl 40. or S rather to the structural portion of the cowl 40 inticated by cross-sectional members 42. The outlet guide vanes 30 connect to the inte8rated cowl 40 and support the core enBine at essentially the same location as in FIG. 2. Each of the vanes 30 is rcleasably connected to a booster casing 44 by bolts or other suitable means (not shown) at the location indicated at 46. The casin~ 44 may be referred to as the forward core cowl and is integral with the frame of the rotor module. The vanes 30 are circumferentially spaced within the cowl 40 and depend radially from an inner surface of the cowl toward the casing 44. At least some of the vanes 30 are affix~d to the structural members 42 at their respective ends adjacent the inner surface of cowl 40. The dependin~
ends of the vanes 30 are adapted for releasable attachment to the casing 44. The vanes 30 thus act as support members or struts for supportin~ at least a portion of the rotor module 12 at least partially within the stator module 14. While the vanes 30 extend substantially perpendicularly with respect to the enBine centerline 23, additional support is provid~d by struts 48 which extend obliquely from a connection point 50 adjacent the affixed ends of vanes to a connection point 52 on the forward core cowl or casing 44. The engine 10 may include a yoke (not - shown) or other mounting arran~ement for releasably attachinR the ends of the struts 48 to tho rotor module lZ.
9 ~ 8 7 FIG. 4 is an exploded view of the en~ine assembly of FIG. 3 which illustrates the ssparable elements of the en~ine. In particular, the fan blades 24 along with the fan spinner 28 are removable from the rotor module 12 and can be disassembled from the rotor module without removing the engine nacelle 40. The blades 24 are preferably individually detachable from a rotatable fan rotor 45 which also is part of the core en8ine and is coaxial with centerline 23. The method of conn~ctin~ or removably attaching the vanas 30 to the fan~rotor 45 may be any of the methods well known to those skilled in the art including methots presently used for attachin3 such fan blades to fan rotors in commercially available turbofan engines.
The fan rotor 45 is attached to the fan shaft 37 (seen in FIC. l) for transferring power from the low pressure turbine stage 22 to the fan blades 24 and booster compressor sta~e 16.
The rotor module 12 is disconnectable or releasable from the vanes 30 and struts 48 at the connection points 46 and 52, r~spectively, leaving the vanes 30 and struts 48 in their affixed dependin~
position as shown in FIG. 4. Note also that the aft core cowl 33 may also be removed from the rotor module 12 to facilitate handling and transportin~ of the rotor module. Other accessory components indicated ~enerally at 58 such as9 for example, an elect~ic generator and a hydraulic pump, may also be removet from the rotor motule 12 for ease of handling. The items which can be remo~ed from the core engine or rotor module 12 also represent items which can be replaced without affectin~ th~ inte~rity of the rotor module and requirin~ test stand operation prior to returning the en8ine to flight status. For en8ine :
- lO- 2~21~7 replacement alone, i.e., to replace only the rokor module 12, it is only necessary to remove the access pan~ls (not shown) in the nacelle 40 to provide access to the connection points of the fan blades 24, outlet guide vanes 30 and struts 48 at the rotor motule.
With the fan blades 24 and spinner 28 removed, the rotor module 12 may be disconnected from the stator module 14 and moved in an aft direction to separate the two components. One advantage of this arran8ement is that the rotor module 12 may be removed from an aircraft without removing the nacelle 40. A more si~nificant advantage is that the rotatin~ components, all of which are inte~ral with the rotor module, are separable from the en~ine 10 as an integral unit, lS i.e., the rotor module 12, so that the op~rational int~rity of the en~ine is not compromised by transporting the rotor motule separately from the stator module.
In use, the en~ine 10 can be fully assembled, performance tested and the fan blades 24 removed for transport. At an aircraft, the en8ine nacelle 40 is installed, followed by connection of the rotor module or core en8ine 12 to the nacelle by means of the forward struts 48 and outlet guide vane~ 30 ant an aft support 56 (the aft support 56 may be substantially identical to aft sUpportc now in commercial u8e for supporting engines such as 10 to an aircraft). The fan blades 24 and spinner 28 are thereafter connected to the en~ine 12 to completa assombly. Alternately, the en~ine 10, or replacement components thereof, may be assembled after transportin~ but prior to installation on an aircraft. Similar}y, while removal of the rotor module 12 provides an advanta~eous method of replacin~ or repairing a core engine, there may be 2~7 .
occasions in which it is desirable to remove the entire engine, i.e., the rotor and stator modules, as an integral unit and perform disassembly after such removal. Both methods are contemplat~d by the pr~ent S invention.
While the principles of the invention have now be~n made clear in an illustrative embodiment, it will become apparent to those skilled in the art that many modifications of the structures, arrangements, and components presented in tho above illustrations may be made in the practice of the invention in order to develop alternate embodiments suitable to specific operatin~ requirements without dep~rting from the spirit and scope of the invention as set forth in the claims which follow.
' ' :
surroundin~ the turbine. In general, some form of structural yoke is attached to the en~ine casing and the structural supports attach to the yoke.
As gas turbine en~ines have beccme more powerful and larger, a concern has develop0d with handlin~ ant lS transporting of such enginas. In particular, engines are now bein~ developed with fans and fan casings having diameters in the range of twelve feet.
Transporting of such engines b~ air or ground i~ not practical with current commercial aircraft and over the road transportation guidelines. Accordingly, it is desirable to provide a method of assembling such engines which permits transport without exceeding aircraft or ground transport size limitations.
The problems associated with handl ing and transporting of such large en~ines extends beyond shipments to the installation, removal, and handling of the ensines in aircraft s*rvicin~. It is therefore further desirable to provide a methot and apparatus for servicing of such engines which overcomes the problems associated with such large diameter fans.
~ 3 ~ 2~2~7 SUMMARY OF THE INVENTION
It is an object of the present invention to provide a method and apparatus for asssmbly and mounting of a hi~h-bypass ratio gas turbine en~ine which overcomes the above mentioned disadvantages of such engines.
It is another object of the present invention to provide a method and apparatus which permits separation of the fan and core en~ine plus boo~t~r without affectin~ acceptance testin8 of the ~ngin~.
It is yet another object of the present invention to provide a method and apparatus for incorporation of a fan shroud into an en8ine nacelle with structural support for the core en8ine derived from the nacelle.
The above and other objects. features and advantages are attained in one form in a high-bypass ratio ~as turbine en~ine in which the fan casing is incorporatet into an aircraft mounted cowling or nacslle and the fan casing is made separable from the core engine without disturbing ass~mbly of the intermediate stage or booster compressor. The nac~lle is modified to become a structural m~mber ant is structurally attached to at least one aircraft frame member or strut. Outlet ~uide vanos, normally couplin~ th~ fan shrout to the boo~ter casing. are connected between the nacelle and tho booster frame to support th~ en~ine within the nacelle. The connectir,3 supports are made separable from the booster casin~ to allow the cor~ enBine plus booster to be removable from the nacelle. Still further, the fan spinner and fan blades are made removable from the en~ine without disturbin~ the booster sta~e or removing the core engine. The entire core en~lne is thus intact and can l3DV-9908 ~ 4 - 2~0~7 be tested as a unit. Ths fan blades can be installed on the en~ine for testing purposes and removed for transporting. Such an arran8ement maintains the integrity of the assembled rotating components, e.~., S the compressor, turbine, booster and fan rotor, while allowing separation of elements which are either non-rotatin3 or do not require a rotating interface, such as, for example, the nacelle, outlet guide vanes and the fan blades. Although the fan blades rotate, their connection is a fixed attachment to the fan rotor and does not require a rotatirg interface.
In another form, the turbine en~ine may be characterized as comprisin~ a ~enerally cylindrical stator module transportable as a sin~le unit and includin8 an inte~rated fan casei fan cowl, and inlet.
The en~ine further comprises a rotor module transportable as a single unit and including a core en8ine with a rotatable fan rotor. The rotor module is removably attachable to the stator module. A
plurality of fan blades i5 removably at~achable to the fan rotor. The stator module may includa a plurality of circumferentially spaced and radially depending fan struts attached at one end along an inner surface of the stator module. Another end of the fan struts may 25 be removably attachable to the rotor module for supporting the rotor module within at least part of the stator module. At least some of th~ fan struts may project substantially perpendicular towart the centerline of the rotor module while others of the fan struts may comprise structural outlet guide vanes which project obliquely toward th0 centerlino of the rotor module. A spinner is desirably removably attached to the fan rotor forwart of the fan blades.
- 5 ~ 7 The invention may b0 further characterized as a method for assembling a turbo-fan en~ine having a rotor module including a core enBine with a rotatable fan rotor and furthsr having a stator module including an inte~rated fan casing. fan cowl and inlet. The method comprises removably attachin8 the rotor motule.
as a sinsle inte8rated unit. to the stator module ant thereafter attaching a plurality of fan blades to the fan rotor. The method may further comprise affixing a plurality of circumferentially spaced fan struts to the stator module with the fan struts extending generally radially from the stator module toward the rotor module and removably attachin~ inner ends of the fan struts to the rotor module for supporting the rotor module at least partially within the stator module.
BRIEF ~ E~ OF THE DRAWINGS
For a botter und~rstanding of the present invention. reference may be had to the following detailed description taken in conjunction with the accompanyin8 drawings in which:
FIG. 1 is a simplified partial cros~-sectional drawing of an exemplary gas turbine engine:
FIG. 2 is a ~implified drawin~ showin~ mounting cf the en8in~ of FIG. 1 on an aircraft win~:
FIC. 3 is a simplified drawing showing an en~ino arran8ement in accordance with the present invention mounted to an aircraft win~; and FIG. 4 i5 an exploded view of the en8ine arran8ement of FIG. 3 showing engine disa-~sembly.
- 6 - 2~21~3 1 DESCRIPTION OF THE PRFFERRED EM~ODIMENT
Referrin3 first to FIG. 1, there is shown a partial cross-sectional drawin~ of an exemplary high-bypass ratio gas turbine en8ine 10 having a core enBine portion indicated at 12 and a fan portion indicated at 14. The core en8ine or core engine portion 12 may be referred to as the rotor module while the fan portion 14 may be referred to as the stator module. In ~eneral, a_ least so~e ext nt of the rotor module lies within the stator module. The rotor module or core engine 12 includes an intermetiate pressure compressor or booster sta~e 16, a high pressure compressor stage 18. a combustor stage 20, a hiBh pressure turbine sta~e 21, and a low lS prsssure turbine stage 22 all aligned on an en8ine centerline 23. The fan portion 14 inclutes a plurality of fan blades 24. a fan shroud 26. a fan spinnsr 28 and a plurality of circumferentially spaced outlet guide vanes 30 which support the fan shroud 26.
The vanes 30 are attached to en8ine casing 32 adjacent the booster stage 16. The en~ine 10 aIso includes an aft core cowl 33 and a primary nozzl~ 35. A fan shaft 37 driv~n by turbine stage 22 extends throu~h the engine and is coupled in drivin~ relationship with booster stage 16 and fan blades 24 via a fan rotor 45.
The high pressure turbine stage 21 drives a compressor stage 18 through a hi~h pressure shaft 41.
As will be apparent from FIG. 1. handling of the engine 10 is a major problem for very largè diamater fan blates 24. While it is possible to remove the blades 24. the practice in the art is to treat the blades 24. booster sta~e 16, and casing 26 as a unitary module. Some engines are constructed with a ~ 7 ~ 2 ~ 210 8 7 two-piece fan shaft 37 separable aft of the boostsr sta~e 16 approximately along the line 43. These en8ines are identified as n sp 1 i t fan~ engines.
Assembly and/or disassembly of split fan engines is complicated since it is difficult to attach the fan forward shaft and the fan mid ~haft properly. In such fan split methods of separating an en~ine. the forward module or fan module includes the fan shroud 26, structural outlet guide vanes 30, fan spinner 28, fan rotor blades 24. alon~ with Ih0 fan rotor. booster sta~e 16 and the forward portion of shaft 37. Thus, it has not been practical to separate the fan module and large external components from the core en8ine to facilitate handlin~. Furthermore, it is not desirable to separate an engine where such separation includes a rotatin8 interface since such interface may involve bearings or critical alignments.
Turnin~ now to FIG. 2. there,is shown a simplified cross-sectional view of an en8ine similar to that of FIG. 1 mounted within an aerodynamic fan cowl 34 which is in turn coupled via a structural member 36 to an aircraft wing 33. The structural m~mber 38 and cowlin~ 34 are well known in the art and may be of the type shown. by way of example, in U.S. Patent No.
~5 4.132.069. Within the fan cowl 34, the member 36 is connected to the fan shroud 26. The shrout 26 is releasably connected to the cowl 34. The cowl 34 preferably includes an inlet section 37.
FIG. 3 illustrates an arranBement in accordance with the tea~hing of the present invention in a stylized repr~sontation of a turbofan en8ine. The fan cowl, indicated at, 40, is an inte~rated cowl incorporating the aerodynamic characteristics of the cowl 34 but incluting the structural features of a fan .
.
- 8 - 2~2~a~7 casin~. In partic~lar, the fan shrout 26 is now an integrated part of cowl 40 as shown by the increased thickness in the cross-sectional dimensions of FIG. 3.
The structural member 36 attaches to the cowl 40. or S rather to the structural portion of the cowl 40 inticated by cross-sectional members 42. The outlet guide vanes 30 connect to the inte8rated cowl 40 and support the core enBine at essentially the same location as in FIG. 2. Each of the vanes 30 is rcleasably connected to a booster casing 44 by bolts or other suitable means (not shown) at the location indicated at 46. The casin~ 44 may be referred to as the forward core cowl and is integral with the frame of the rotor module. The vanes 30 are circumferentially spaced within the cowl 40 and depend radially from an inner surface of the cowl toward the casing 44. At least some of the vanes 30 are affix~d to the structural members 42 at their respective ends adjacent the inner surface of cowl 40. The dependin~
ends of the vanes 30 are adapted for releasable attachment to the casing 44. The vanes 30 thus act as support members or struts for supportin~ at least a portion of the rotor module 12 at least partially within the stator module 14. While the vanes 30 extend substantially perpendicularly with respect to the enBine centerline 23, additional support is provid~d by struts 48 which extend obliquely from a connection point 50 adjacent the affixed ends of vanes to a connection point 52 on the forward core cowl or casing 44. The engine 10 may include a yoke (not - shown) or other mounting arran~ement for releasably attachinR the ends of the struts 48 to tho rotor module lZ.
9 ~ 8 7 FIG. 4 is an exploded view of the en~ine assembly of FIG. 3 which illustrates the ssparable elements of the en~ine. In particular, the fan blades 24 along with the fan spinner 28 are removable from the rotor module 12 and can be disassembled from the rotor module without removing the engine nacelle 40. The blades 24 are preferably individually detachable from a rotatable fan rotor 45 which also is part of the core en8ine and is coaxial with centerline 23. The method of conn~ctin~ or removably attaching the vanas 30 to the fan~rotor 45 may be any of the methods well known to those skilled in the art including methots presently used for attachin3 such fan blades to fan rotors in commercially available turbofan engines.
The fan rotor 45 is attached to the fan shaft 37 (seen in FIC. l) for transferring power from the low pressure turbine stage 22 to the fan blades 24 and booster compressor sta~e 16.
The rotor module 12 is disconnectable or releasable from the vanes 30 and struts 48 at the connection points 46 and 52, r~spectively, leaving the vanes 30 and struts 48 in their affixed dependin~
position as shown in FIG. 4. Note also that the aft core cowl 33 may also be removed from the rotor module 12 to facilitate handling and transportin~ of the rotor module. Other accessory components indicated ~enerally at 58 such as9 for example, an elect~ic generator and a hydraulic pump, may also be removet from the rotor motule 12 for ease of handling. The items which can be remo~ed from the core engine or rotor module 12 also represent items which can be replaced without affectin~ th~ inte~rity of the rotor module and requirin~ test stand operation prior to returning the en8ine to flight status. For en8ine :
- lO- 2~21~7 replacement alone, i.e., to replace only the rokor module 12, it is only necessary to remove the access pan~ls (not shown) in the nacelle 40 to provide access to the connection points of the fan blades 24, outlet guide vanes 30 and struts 48 at the rotor motule.
With the fan blades 24 and spinner 28 removed, the rotor module 12 may be disconnected from the stator module 14 and moved in an aft direction to separate the two components. One advantage of this arran8ement is that the rotor module 12 may be removed from an aircraft without removing the nacelle 40. A more si~nificant advantage is that the rotatin~ components, all of which are inte~ral with the rotor module, are separable from the en~ine 10 as an integral unit, lS i.e., the rotor module 12, so that the op~rational int~rity of the en~ine is not compromised by transporting the rotor motule separately from the stator module.
In use, the en~ine 10 can be fully assembled, performance tested and the fan blades 24 removed for transport. At an aircraft, the en8ine nacelle 40 is installed, followed by connection of the rotor module or core en8ine 12 to the nacelle by means of the forward struts 48 and outlet guide vane~ 30 ant an aft support 56 (the aft support 56 may be substantially identical to aft sUpportc now in commercial u8e for supporting engines such as 10 to an aircraft). The fan blades 24 and spinner 28 are thereafter connected to the en~ine 12 to completa assombly. Alternately, the en~ine 10, or replacement components thereof, may be assembled after transportin~ but prior to installation on an aircraft. Similar}y, while removal of the rotor module 12 provides an advanta~eous method of replacin~ or repairing a core engine, there may be 2~7 .
occasions in which it is desirable to remove the entire engine, i.e., the rotor and stator modules, as an integral unit and perform disassembly after such removal. Both methods are contemplat~d by the pr~ent S invention.
While the principles of the invention have now be~n made clear in an illustrative embodiment, it will become apparent to those skilled in the art that many modifications of the structures, arrangements, and components presented in tho above illustrations may be made in the practice of the invention in order to develop alternate embodiments suitable to specific operatin~ requirements without dep~rting from the spirit and scope of the invention as set forth in the claims which follow.
' ' :
Claims (16)
1. A high-bypass ratio gas turbine engine having a core engine portion and a fan, the core engine portion including a casing for structurally supporting the core engine portion, the engine being adapted for mounting in an aerodynamic nacelle supported on an aircraft, the improvement comprising:
a fan shroud integrated into the nacelle, the nacelle including structural members for supporting at least a portion of the core engine:
a plurality of support members connected to the nacelle to the engine casing, said support members being releasably connected to the casing; and moans for releasably connecting the fan to the core engine.
a fan shroud integrated into the nacelle, the nacelle including structural members for supporting at least a portion of the core engine:
a plurality of support members connected to the nacelle to the engine casing, said support members being releasably connected to the casing; and moans for releasably connecting the fan to the core engine.
2. The gas turbine engine of claim 1 wherein said support members comprise outlet guide vanes.
3. The gas turbine engine of claim 1 and including a fan spinner releasably coupled to said fan blades.
4. The gas turbine engine of claim 1 wherein said fan shroud comprises a structural member of said nacelle.
5. A method for assembling a high-bypass ratio gas turbine engine to an aircraft, the aircraft including an aerodynamic nacelle for receiving the engine, the nacelle including an integral cylindrical fan shroud forming a structural support portion of the nacelle and further including structural members for attaching the nacelle to the aircraft, the engine including a core portion and a detachable fan, the core portion being encased within a structural casing, the method comprising the steps of:
connecting a plurality of radially directed engine support members to an inner surface of the structural support portion of the fairing;
positioning the core engine within the support members;
connecting each of the support members to the engine casing to support at least one end of the engine within the fairing; and attaching the fan blades to the engine positioned so as to rotate within the integral shrouds.
connecting a plurality of radially directed engine support members to an inner surface of the structural support portion of the fairing;
positioning the core engine within the support members;
connecting each of the support members to the engine casing to support at least one end of the engine within the fairing; and attaching the fan blades to the engine positioned so as to rotate within the integral shrouds.
6. The method of claim 5 and including the step of attaching a fan spinner to the fan.
7. A method for removing a high-bypass gas turbine engine from a structural nacelle in which at least a portion of the nacelle acts as a fan shroud, the engine including a fan and a core portion with the core portion being supported by outlet guide vanes attached to the nacelle. the method comprising the steps of:
removing a fan spinner from the engine:
disconnecting each of the fan blades from the engine and removing each successively from within the nacelle:
uncoupling each of the outlet guide vanes from its corresponding connection to the engine casing;
detaching an aft engine support; and sliding the engine in an aft direction out of the nacelle and removing the detach engine from the aircraft.
removing a fan spinner from the engine:
disconnecting each of the fan blades from the engine and removing each successively from within the nacelle:
uncoupling each of the outlet guide vanes from its corresponding connection to the engine casing;
detaching an aft engine support; and sliding the engine in an aft direction out of the nacelle and removing the detach engine from the aircraft.
8. A turbofan engine comprising:
a stator module transportable as a single unit and including an integrated fan case, fan cowl. and inlet:
a rotor module transportable as a single unit and including a core engine with a rotatable fan rotor;
means for removably attaching said rotor module to said stator module; and a plurality of fan blades removably attached to said fan rotor.
a stator module transportable as a single unit and including an integrated fan case, fan cowl. and inlet:
a rotor module transportable as a single unit and including a core engine with a rotatable fan rotor;
means for removably attaching said rotor module to said stator module; and a plurality of fan blades removably attached to said fan rotor.
9. The turbofan engine of claim 8 wherein said stator module also includes. integrated therewith. a plurality of fan struts each having a free end, and wherein said means include means for removably attaching said rotor module to said free ends of said fan struts.
10. The turbofan engine of claim 9 wherein at least some of said fan struts comprise structural outlet guide vanes which project generally perpendicularly toward the centerline of said stator module.
11. The turbofan engine of claim 10 wherein the remainder of said fan struts project generally obliquely toward the centerline of said stator module.
12. The turbofan engine of claim 8 also including a spinner removably attached to said fan rotor.
13. A turbofan engine comprising:
a stator module transportable as a single unit ant including an intergated fan case. fan cowl, inlet, and plurality of fan struts each having a free end wherein at least some of said fan struts comprise structural outlet guide vanes which project generally perpendicularly toward the centerline of said stator module and the remainder of said fans struts project generally obliquely toward the centerline of said stator module:
a rotor module transportable as a single unit and including a core engine with a rotatable fan rotor;
means for removably attaching said rotor module to said free ends of said frame struts;
a plurality of fan blades removably attached to said fan rotor; and a spinner removably attached to said fan rotor.
a stator module transportable as a single unit ant including an intergated fan case. fan cowl, inlet, and plurality of fan struts each having a free end wherein at least some of said fan struts comprise structural outlet guide vanes which project generally perpendicularly toward the centerline of said stator module and the remainder of said fans struts project generally obliquely toward the centerline of said stator module:
a rotor module transportable as a single unit and including a core engine with a rotatable fan rotor;
means for removably attaching said rotor module to said free ends of said frame struts;
a plurality of fan blades removably attached to said fan rotor; and a spinner removably attached to said fan rotor.
14. A method for assembling a turbofan engine having a rotor module including a core engine with a rotatable fan rotor and having a stator module including an integrated fan case. fan cowl. ant inlet.
said method comprising the steps of:
removably attaching said rotor module as a single unit to said stator module: and removably attaching a plurality of fan blades to said fan rotor.
said method comprising the steps of:
removably attaching said rotor module as a single unit to said stator module: and removably attaching a plurality of fan blades to said fan rotor.
15. A method for assembling a turbofan engine having a rotor module including a core engine with a rotatable fan rotor and having a stator module including an integrated fan case, fan cowl. inlet. and plurality of fan struts each having a free end, said method comprising the steps of:
removably attaching said rotor module as a single unit to said free ends of said fan struts: and removably attaching a plurality of fan blades to said fan rotor.
removably attaching said rotor module as a single unit to said free ends of said fan struts: and removably attaching a plurality of fan blades to said fan rotor.
16. The invention as defined in any of the preceding claims including any further features of novelty disclosed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US40397489A | 1989-09-07 | 1989-09-07 | |
| US403,974 | 1989-09-07 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2021087A1 true CA2021087A1 (en) | 1991-03-08 |
Family
ID=23597620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002021087A Abandoned CA2021087A1 (en) | 1989-09-07 | 1990-07-12 | Ultra high bypass engine integrated fan/cowl and transportation/removal |
Country Status (6)
| Country | Link |
|---|---|
| JP (1) | JPH03141829A (en) |
| CA (1) | CA2021087A1 (en) |
| DE (1) | DE4025775A1 (en) |
| FR (1) | FR2651537A1 (en) |
| GB (1) | GB2238082A (en) |
| IT (1) | IT1242998B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2866070B1 (en) * | 2004-02-05 | 2008-12-05 | Snecma Moteurs | TURBOREACTOR WITH HIGH DILUTION RATE |
| GB0520850D0 (en) | 2005-10-14 | 2005-11-23 | Rolls Royce Plc | Fan static structure |
| US20100047077A1 (en) * | 2007-12-28 | 2010-02-25 | General Electric Company | Ferry Flight Engine Fairing Kit |
| US20100043228A1 (en) * | 2007-12-28 | 2010-02-25 | James Lloyd Daniels | Method of Preparing an Engine for Ferry Flight |
| US8469309B2 (en) | 2008-12-24 | 2013-06-25 | General Electric Company | Monolithic structure for mounting aircraft engine |
| US8814512B2 (en) | 2011-07-05 | 2014-08-26 | United Technologies Corporation | Fan disk apparatus and method |
| CN107738223B (en) * | 2017-11-13 | 2023-11-10 | 山东太古飞机工程有限公司 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
| GB201810606D0 (en) * | 2018-06-28 | 2018-08-15 | Rolls Royce Plc | Gas turbine engine |
| GB201817935D0 (en) * | 2018-11-02 | 2018-12-19 | Rolls Royce Plc | Method of replacing a module |
| GB201817936D0 (en) * | 2018-11-02 | 2018-12-19 | Rolls Royce Plc | Method of upgrading a modular gas turbine engine |
| GB202001971D0 (en) * | 2020-02-13 | 2020-04-01 | Rolls Royce Plc | Nacelle for gas turbine engine and aircraft comprising the same |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1093050A (en) * | 1965-03-16 | 1967-11-29 | Rolls Royce | Aircraft engine mounting |
| US3398535A (en) * | 1966-05-25 | 1968-08-27 | Gen Electric | Engine supporting structure |
| FR2153787A5 (en) * | 1971-09-23 | 1973-05-04 | Inst Francais Du Petrole | |
| FR2096708B1 (en) * | 1970-06-22 | 1974-03-22 | Snecma | |
| US3703081A (en) * | 1970-11-20 | 1972-11-21 | Gen Electric | Gas turbine engine |
| JPS5022165U (en) * | 1973-06-23 | 1975-03-12 | ||
| GB1533551A (en) * | 1974-11-08 | 1978-11-29 | Gen Electric | Gas turbofan engines |
| JPS5268609A (en) * | 1975-12-04 | 1977-06-07 | Agency Of Ind Science & Technol | Fixing device for static wing in turbo-fan engine |
| US4825648A (en) * | 1987-03-02 | 1989-05-02 | General Electric Company | Turbofan engine having a split cowl |
| US4934140A (en) * | 1988-05-13 | 1990-06-19 | United Technologies Corporation | Modular gas turbine engine |
-
1990
- 1990-07-12 CA CA002021087A patent/CA2021087A1/en not_active Abandoned
- 1990-08-14 DE DE4025775A patent/DE4025775A1/en not_active Ceased
- 1990-08-22 FR FR9010566A patent/FR2651537A1/en not_active Withdrawn
- 1990-08-28 JP JP2224523A patent/JPH03141829A/en active Pending
- 1990-08-30 IT IT02133690A patent/IT1242998B/en active IP Right Grant
- 1990-09-05 GB GB9019356A patent/GB2238082A/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| JPH03141829A (en) | 1991-06-17 |
| DE4025775A1 (en) | 1991-03-28 |
| FR2651537A1 (en) | 1991-03-08 |
| IT9021336A0 (en) | 1990-08-30 |
| GB9019356D0 (en) | 1990-10-17 |
| GB2238082A (en) | 1991-05-22 |
| IT9021336A1 (en) | 1992-03-01 |
| IT1242998B (en) | 1994-05-23 |
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Legal Events
| Date | Code | Title | Description |
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| FZDE | Discontinued |