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WO2013130373A1 - Architecture de corps central avant pour moteur à turbine à gaz - Google Patents

Architecture de corps central avant pour moteur à turbine à gaz Download PDF

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Publication number
WO2013130373A1
WO2013130373A1 PCT/US2013/027557 US2013027557W WO2013130373A1 WO 2013130373 A1 WO2013130373 A1 WO 2013130373A1 US 2013027557 W US2013027557 W US 2013027557W WO 2013130373 A1 WO2013130373 A1 WO 2013130373A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
turbine engine
support
central body
body support
Prior art date
Application number
PCT/US2013/027557
Other languages
English (en)
Inventor
John R. Otto
Brian P. Cigal
Sunil Sharma
Original Assignee
United Technologies Corporation
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from US13/407,916 external-priority patent/US8360714B2/en
Application filed by United Technologies Corporation filed Critical United Technologies Corporation
Priority to SG11201404988VA priority Critical patent/SG11201404988VA/en
Publication of WO2013130373A1 publication Critical patent/WO2013130373A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/72—Maintenance
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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

  • the present disclosure relates to a gas turbine engine, and in particular, to a case structure therefor.
  • Gas turbine engines typically include one or more rotor shafts that transfer power and rotary motion from a turbine section to a compressor section and fan section.
  • the rotor shafts are supported within an engine static structure, which is typically constructed of modules with individual case sections which are joined together at bolted flanges.
  • the flanges form a joint capable of withstanding the variety of loads transmitted through the engine static structure.
  • a gas turbine engine in one exemplary embodiment, includes a central body support that provides an inner annular wall for a core flow path.
  • the central body support includes first splines.
  • a geared architecture interconnects a spool and a fan rotatable about an axis.
  • a flex support interconnects the geared architecture to the central body support.
  • the flex support includes second splines that intermesh with the first splines for transferring torque there between.
  • the central body support includes circumferentially spaced apart vanes that radially extend between and interconnect the inner annular wall and an outer annular wall.
  • the first splines include tooth groups including multiple teeth.
  • the tooth groups are circumferentially spaced apart from one another with untoothed regions arranged between the tooth groups.
  • the vanes are circumferentially aligned with the untoothed regions.
  • the second splines include corresponding tooth groups that are configured to circumferentially align and mate with the tooth groups of the first splines, and corresponding untoothed regions are arranged between the tooth groups of the corresponding tooth groups.
  • the central body support includes multiple fastener bosses that are circumferentially spaced from one another.
  • the clusters of fastener bosses are aligned with the tooth groups.
  • the untoothed region is provided by a stiffening rail protruding radially inward from a central body section that provides the inner annular wall.
  • the central body support includes an annular recess and an annular pocket that are axially spaced apart from one another to provide first and second lateral sides on the stiffening rail.
  • the tooth groups include internal teeth that have roots provided at a first tooth radius and extend radially inward to crests provided at a second tooth radius.
  • the stiffening rail extends radially inward to a rail radius that is less than the first tooth radius.
  • the geared architecture includes an epicyclic gear train having a sun gear, a ring gear, and intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear.
  • the intermediate gears are star gears grounded to the flex support against rotation about the axis.
  • the sun gear is supported by the spool, and the ring gear is interconnected to the fan.
  • the central body support includes a first inner face arranged near the first spline
  • the flex support includes a first outer face arranged in an interference fit relationship with the first inner face to radially locate the flex support relative to the central body support.
  • the central body support includes a second inner face
  • the flex support includes a second outer face arranged in an interference fit relationship with the second inner face.
  • the first inner and outer faces are arranged forward of the first spline and the second inner and outer faces are arranged aft of the first spline.
  • the second outer face is positioned radially inward relative to the first outer face.
  • fasteners secure the flex support to the central body support, and the fasteners include heads facing forward.
  • the central body support includes circumferentially spaced fastener bosses
  • the flex support includes a radially outward extending fastener flange that abuts the fastener bosses to axially locate the flex support relative to the central body support.
  • the fastener flange includes apertures that are arranged circumferentially spaced from one another and receive the fasteners.
  • a method of disassembling a front architecture of a gas turbine engine includes the step of accessing forward-facing fasteners that secure a central body support to a flex support.
  • the flex support includes a geared architecture supported thereon.
  • the method also includes the steps of removing the fasteners, and decoupling first and second splines respectively provided on the central body support and the flex support.
  • the accessing step includes the step of detaching a fan module from a fan shaft bearing support, with the fan shaft bearing support remaining secured to the central body support.
  • the accessing step includes the step of detaching the fan shaft bearing support from the central support body without removing the geared architecture.
  • the decoupling step includes removing a geared architecture module that includes the geared architecture and the flex support.
  • the decoupling step leaves undisturbed a bearing that supports a front of a spool operatively connectable with the geared architecture.
  • Figure 1 is a schematic cross-section of an embodiment of a gas turbine engine
  • Figure 2 is an enlarged cross-section of a front center body assembly portion of the gas turbine engine embodiment shown in Figure Is;
  • Figure 3 is an enlarged cross-section of the geared architecture of the gas turbine engine embodiment shown in Figure 1 ;
  • Figure 4 is an exploded perspective view of the front center body assembly of the turbine engine embodiment shown in Figure 1 ;
  • Figure 5 is an enlarged perspective partial cross-section of a front center body support of the front center body assembly of the turbine engine embodiment shown in Figure 1;
  • Figure 6 is an enlarged sectional view of the front center body support of the turbine engine embodiment shown in Figure 1 ;
  • Figure 6 A is a perspective view of the center body support of the turbine engine embodiment shown in Figure 1 ;
  • Figure 6B is an end view of the center body support of the turbine engine embodiment shown in Figure 1 ;
  • Figure 7 is an exploded view of the front center body support of the turbine engine embodiment shown in Figure 1 ;
  • Figure 8 is a schematic view of an embodiment of a forward gearbox removal from a gas turbine engine.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmentor section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flowpath B while the compressor section 24 drives air along a core flowpath C for compression and communication into the combustor section 26 then expansion through the turbine section 28.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmentor section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flowpath B while the compressor section 24 drives air along a core flowpath C for compression and communication into the comb
  • the engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure (or first) compressor section 44 and a low pressure (or first) turbine section 46.
  • the inner shaft 40 is connected to the fan 42 through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
  • a #2 bearing support 38A located within the compressor section 24 supports a forward end of the inner shaft 40. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.
  • the high speed spool 32 includes an outer shaft 50 that interconnects a high pressure (or first) compressor section 52 and high pressure (or first) turbine section 54.
  • a combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54.
  • a "high pressure” compressor or turbine experiences a higher pressure than a corresponding "low pressure” compressor or turbine.
  • the core airflow C is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46.
  • the turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
  • the engine 20 in one example is a high-bypass geared aircraft engine.
  • the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine 46 has a pressure ratio that is greater than about 5.
  • the geared architecture 48 includes a sun gear, a ring gear, and intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear.
  • the intermediate gears are star gears grounded to a flex support 68 (shown in Figure 6) against rotation about the axis A.
  • the sun gear is supported by the low speed spool 30, and the ring gear is interconnected to the fan 42.
  • the engine 20 bypass ratio is greater than about ten (10: 1), the fan diameter is significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 has a pressure ratio that is greater than about 5: 1.
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
  • the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.5:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
  • a significant amount of thrust is provided by a bypass flow B due to the high bypass ratio.
  • the fan section 22 of the engine 20 is designed for a particular flight condition - typically cruise at about 0.8 Mach and about 35,000 feet.
  • the flight condition of 0.8 Mach and 35,000 ft, with the engine at its best fuel consumption - also known as "bucket cruise Thrust Specific Fuel Consumption ('TSFC')" - is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point.
  • "Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non- limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tambient deg R) / 518.7) ⁇ 0.5].
  • the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft / second.
  • the above parameters for the engine 20 are intended to be exemplary.
  • the engine static structure 36 proximate the compressor section 24 includes a front center body assembly 60 adjacent to the #2 bearing support 38 A.
  • the front center body assembly 60 generally includes a front center body support 62.
  • the #2 bearing support 38A generally includes a seal package 64, a bearing package 66 and a centering spring 70.
  • a flex support 68 provides a flexible attachment of the geared architecture 48 within the front center body support 62 (also illustrated in Figure 4).
  • the flex support 68 reacts the torsional loads from the geared architecture 48 and facilitates vibration absorption as well as other support functions.
  • the centering spring 70 is a generally cylindrical cage-like structural component with a multiple of beams that extend between flange end structures (also illustrated in Figure 4). The centering spring 70 resiliently positions the bearing package 66 with respect to the low spool 30.
  • the beams are double-tapered beams arrayed circumferentially to control a radial spring rate that may be selected based on a plurality of considerations including, but not limited to, bearing loading, bearing life, rotor dynamics, and rotor deflection considerations.
  • the front center body support 62 includes a front center body section 72 and a bearing section 74 defined about axis A with a frustro-conical interface section 76 therebetween (Figure 5).
  • the front center body section 72 at least partially defines the core flowpath into the low pressure compressor 44.
  • the front center body section 72 includes an annular core passage with circumferentially arranged front center body vanes 71 having leading and trailing edges 72A, 72B shown in section in Figure 3.
  • the bearing section 74 is defined radially inward of the front center body section 72.
  • the bearing section 74 locates the bearing package 66 and the seal package 64 with respect to the low spool 30.
  • the frustro- conical interface section 76 combines the front center body section 72 and the bearing section 74 to form a unified load path, substantially free of kinks typical of a conventional flange joint, from the bearing package 66 to the outer periphery of the engine static structure 36.
  • the frustro-conical interface section 76 may include a weld W ( Figure 5) or, alternatively, be an integral section such that the front center body support 62 is a unitary component.
  • the integral, flange-less arrangement of the frustro-conical interface section 76 facilitates a light weight, reduced part count architecture with an increased ability to tune the overall stiffness and achieve rotor dynamic requirements.
  • Such an architecture also further integrates functions such as oil and air delivery within the bearing compartment which surrounds bearing package 66.
  • the front center body support 62 includes mount features to receive the flex support 68.
  • the flex support 68 includes a conical support 158 that supports an integral flex member 160, which provides a fold for absorbing vibrations.
  • the mount features of the front center body support 62 includes first splines 78, which are internal in the example, and radially inward directed fastener bosses 80 on the front center body section 72.
  • the flex support 68 includes corresponding second splines 82, which are external in the example, and radially outwardly directed fastener flange 84.
  • the flex support 68 is received into the front center body support 62 at a splined interface 86 formed by first and second splines 78, 82 and retained therein such that fastener flange 84 abuts fastener bosses 80.
  • the splined interface 86 transfers torque between the first and second splines 78, 82.
  • a set of fasteners 88 such as bolts, are threaded into the fastener bosses 80 and the fastener flange 84 to mount the flex support 68 within the front center body support 62.
  • the fasteners 88 include heads 89 facing forward for access from the front of the engine 20.
  • the central body support 62 provides an inner annular wall 128 for the core airflow C.
  • the vanes 71 interconnect the inner annular wall 128 to an outer annular wall 129 to provide a unitary structure.
  • the first splines 78 include tooth groups 146 including multiple teeth.
  • the tooth groups 146 are circumferentially spaced apart from one another with untoothed regions arranged between the tooth groups 146.
  • the vanes 71 are circumferentially aligned with an untoothed region to structurally reinforce the interface between the first and second splines 78, 82.
  • the second splines 82 include corresponding tooth groups that are configured to circumferentially align and mate with the tooth groups 146 of the first splines 146. Corresponding untoothed regions are arranged between the tooth groups of the second splines 82.
  • the fastener bosses 80 are arranged in clusters circumferentially spaced from one another, as shown in Figure 6A.
  • the fastener bosses 80 are aligned with the tooth groups 146.
  • the fastener bosses 80 may be arranged in other configurations.
  • the fastener flange 84 extends radially outward from an annular flange 127 that axially extends from the second splines 82.
  • the fastener flange 84 includes an aft surface 142 that abuts a face 144 of the fastener bosses 80 to axially locate the flex support 68 relative to the central body support 62.
  • the fastener flange 84 includes apertures 132 that are arranged in clusters circumferentially spaced from one another and receive the fasteners 88, which are secured in holes 130 of the fastener bosses 80.
  • the fastener flange 84 may include interruptions or recesses that permit componentry to pass through the flex support 68 at the perimeter of the fasteners flange 84.
  • the untoothed region 146 is provided by a stiffening rail 148 protruding radially inward from the central body section 72 that provides the inner annular wall 128.
  • the central body support 62 includes an annular recess 150 and an annular pocket 152 that are axially spaced apart from one another to provide first and second lateral sides 154, 156 on the stiffening rail 148.
  • the teeth of the tooth groups 146 include roots provided at a first tooth radius Tl and extend radially inward to crests provided at a second tooth radius T2.
  • the stiffening rail 148 extends radially inward to a rail radius R that is less than the first tooth radius Tl, and in one example, equal to the second tooth radius T2.
  • the stiffening rail 148 and its circumferential alignment with the vanes 71 ensures improved cylindricity of the central body section 72 during engine operation.
  • the central body support 62 includes a first inner face 134 arranged near the first spline 78 and is provided by the annular recess 150.
  • the flex support 68 includes a first outer face 138 arranged in an interference fit relationship at room temperature with the first inner face 134 to radially locate the flex support 68 relative to the central body support 62.
  • a second inner face 136 is provided on the central body support 62, and the flex support 68 includes a second outer face 140 arranged in an interference fit relationship at room temperature with the second inner face 136.
  • the first inner and outer faces 134, 138 are arranged forward of the first spline 78, and the second inner and outer faces 136, 140 are arranged aft of the first spline 78.
  • the second outer face 140 is smaller than the first outer face 138 to facilitate assembly and disassembly of the flex support 68 from the front of the engine 20.
  • the heads 89 of the fasteners 88 are directed forward to provide access from a forward section of the front center body assembly 60 opposite the bearing package 66 of the number two bearing system 38A.
  • the fasteners 88 are thereby readily removed to access a gearbox 90 of the geared architecture 48.
  • a fan shaft bearing support front wall 102 aft of the fan 42 is mounted to a forward section of the front center body support 62 to provide access to the geared architecture 48 from the front of the engine 20.
  • the front wall 102 includes a flange 103 mountable to the front center body support 62 at the flange 61 by a multiple of fasteners 105, which fasteners 105 may in one non-limiting embodiment be bolts.
  • the front wall 102 and the front center body support 62 define a bearing compartment 100 (also shown in Figure 2) which mounts to the bearing package 66.
  • the front wall 102 is removable such that the gearbox 90 may be accessed as a module. The gearbox 90 may thereby be accessed to facilitate rapid on-wing service.
  • bearing structures 104 (illustrated schematically and in Figure 2) and seals 106 (illustrated schematically and in Figure 2) may be supported by the front wall 102 to contain oil and support rotation of an output shaft 108.
  • the output shaft 108 connects with the geared architecture 48 to drive the fan 42.
  • Fan blades 42B extend from a fan hub 110 which are mounted to the output shaft 108 for rotation therewith.
  • the bearing structures 104 and seals 106 may, in the disclosed non- limiting embodiment may be disassembled with the front wall 102 as a unit after removal of the fan hub 110.
  • the gearbox 90 is driven by the low spool 30 ( Figure 1) through a coupling shaft 112.
  • the coupling shaft 112 transfers torque through the bearing package 66 to the gearbox 90 as well as facilitates the segregation of vibrations and other transients.
  • the coupling shaft 112 generally includes a forward coupling shaft section 114 and an aft coupling shaft section 116 which extends from the bearing package 66, however, more or fewer pieces may be used to provide the coupling shaft 112.
  • the forward coupling shaft section 114 includes an interface spline 118 which mates with an aft spline 120 of the aft coupling shaft section 116.
  • An interface spline 122 of the aft coupling shaft section 116 connects the coupling shaft 112 to the low spool 30 through, in this non limiting embodiment, splined engagement with a spline 124 on a low pressure compressor hub 126 of the low pressure compressor 44.
  • the front architecture of the engine 20 is disassembled by detaching the fan module from a fan shaft bearing support.
  • the fan shaft bearing support (front wall 102) remains secured to the central body support 62 over the gear box 90.
  • the fan shaft bearing support (front wall 102) is detached from the central support body 62 without removing the gear box 90.
  • the forward-facing fasteners 88 are accessed and removed.
  • the first and second splines 78, 82 are decoupled, and the gear box 90 is removed with the fan shaft bearing support (front wall 102) and the flex support 68.
  • the bearing 38A is left undisturbed.
  • the fan hub 110 is disassembled from the output shaft 108.
  • the multiple of fasteners 105 are then removed such that the front wall 102 is disconnected from the front center body support 62; the front wall 102 is thereafter removed from the engine.
  • the multiple of fasteners 88 are then removed from the front of the engine 20.
  • the geared architecture 48 is then slid forward out of the front center body support 62 such that the interface spline 118 is slid off the aft spline 120 and the outer spline 82 is slid off the internal spline 78.
  • the geared architecture 48 is thereby removable from the engine 20 as a module ( Figure 8; illustrated schematically).
  • the geared architecture 48 is removable from the engine 20 as a module and does not need to be further disassembled. Moreover, although the geared architecture 48 must be removed from the engine to gain access to the bearing package 66 and the seal 64, the geared architecture 48 does not need to be removed from the engine 20 to gain access to the engine core itself.

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  • 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

Moteur à turbine à gaz comprenant un support de corps central qui fournit une paroi annulaire intérieure pour un chemin d'écoulement primaire. Le support de corps central comprend les premières cannelures. Une architecture à engrenages relie une bobine et un ventilateur pouvant pivoter autour d'un axe. Un support flexible relie l'architecture à engrenages au support de corps central. Le support flexible comprend de secondes cannelures qui s'imbriquent dans les premières cannelures pour transférer un couple entre eux.
PCT/US2013/027557 2012-02-29 2013-02-25 Architecture de corps central avant pour moteur à turbine à gaz WO2013130373A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SG11201404988VA SG11201404988VA (en) 2012-02-29 2013-02-25 Gas turbine engine front center body architecture

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/407,916 US8360714B2 (en) 2011-04-15 2012-02-29 Gas turbine engine front center body architecture
US13/407,916 2012-02-29

Publications (1)

Publication Number Publication Date
WO2013130373A1 true WO2013130373A1 (fr) 2013-09-06

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SG (1) SG11201404988VA (fr)
WO (1) WO2013130373A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2539909C1 (ru) * 2013-12-13 2015-01-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Упругодемпферная опора ротора турбомашины
RU2540208C1 (ru) * 2013-10-01 2015-02-10 Открытое акционерное общество "Авиадвигатель" Упругодемпферная опора турбины
WO2019158883A1 (fr) * 2018-02-19 2019-08-22 Safran Aircraft Engines Assemblage de maintien d'un train d'engrenages dans une turbomachine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3922852A (en) * 1973-10-17 1975-12-02 Gen Electric Variable pitch fan for gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3922852A (en) * 1973-10-17 1975-12-02 Gen Electric Variable pitch fan for gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2540208C1 (ru) * 2013-10-01 2015-02-10 Открытое акционерное общество "Авиадвигатель" Упругодемпферная опора турбины
RU2539909C1 (ru) * 2013-12-13 2015-01-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Упругодемпферная опора ротора турбомашины
WO2019158883A1 (fr) * 2018-02-19 2019-08-22 Safran Aircraft Engines Assemblage de maintien d'un train d'engrenages dans une turbomachine
FR3078110A1 (fr) * 2018-02-19 2019-08-23 Safran Aircraft Engines Assemblage de maintien d'un train d'engrenages dans une turbomachine
CN111742128A (zh) * 2018-02-19 2020-10-02 赛峰航空器发动机 用于在涡轮机中保持齿轮系的组件
US11591970B2 (en) 2018-02-19 2023-02-28 Safran Aircraft Engines Assembly for retaining a gear train in a turbomachine
CN111742128B (zh) * 2018-02-19 2024-01-12 赛峰航空器发动机 用于在涡轮机中保持齿轮系的组件

Also Published As

Publication number Publication date
SG11201404988VA (en) 2014-09-26

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