EP2546460A2 - Moteur à turbine et son dispositif de réduction de charge - Google Patents

Moteur à turbine et son dispositif de réduction de charge Download PDF

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Publication number
EP2546460A2
EP2546460A2 EP12165454A EP12165454A EP2546460A2 EP 2546460 A2 EP2546460 A2 EP 2546460A2 EP 12165454 A EP12165454 A EP 12165454A EP 12165454 A EP12165454 A EP 12165454A EP 2546460 A2 EP2546460 A2 EP 2546460A2
Authority
EP
European Patent Office
Prior art keywords
fan
disk
shaft
fan shaft
coupled
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.)
Withdrawn
Application number
EP12165454A
Other languages
German (de)
English (en)
Other versions
EP2546460A3 (fr
Inventor
Tod Robert Steen
Weize Kang
David Paul Adam
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2546460A2 publication Critical patent/EP2546460A2/fr
Publication of EP2546460A3 publication Critical patent/EP2546460A3/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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

Definitions

  • This invention relates generally to gas turbine engines and more specifically to bearing assemblies and load reduction devices for gas turbine engines.
  • a gas turbine engine includes a turbomachinery core having a high pressure compressor, combustor, and high pressure turbine in serial flow relationship.
  • the core is operable in a known manner to generate a primary flow of propulsive gas.
  • a typical turbofan engine adds a low pressure turbine driven by the core exhaust gases which in turn drives a fan rotor through a shaft to generate a bypass flow of propulsive gas. In the case of a high bypass engine this provides the majority of the total engine thrust.
  • the fan rotor includes a fan that includes an array of fan blades extending radially outward from a fan disk.
  • the fan shaft transfers power and rotary motion from the low pressure turbine to the fan disk and is supported in several rolling-element bearing assemblies spaced along its length.
  • the bearings are commonly referred to as no. 1, no. 2, and no. 5 bearings, identifying their sequential position in the engine.
  • a fragment of a fan blade may become separated from the remainder of the blade as a result of impact with a foreign object. Accordingly, a substantial rotary unbalance load may be created within the damaged fan and carried by the bearings, bearing supports, and the fan support frames.
  • known engines include support components for the fan rotor support system that are sized to provide additional strength for the fan support system.
  • increasing the strength of the support components undesirably increases an overall weight of the engine and decreases an overall efficiency of the engine when the engine is operated without substantial rotor imbalances.
  • LRD load reduction device
  • the invention provides a fan rotor apparatus including: a rotatable fan disk defining a central aperture and carrying an array of airfoil-shaped fan blades around its periphery, the disk having a forward end and an aft end; ⁇ an annular, generally axially-extending forward fan shaft extending through the aperture and coupled to the fan disk for rotation therewith, where the forward fan shaft joins the fan disk at or near the forward end.
  • a turbofan engine includes: a turbomachinery core operable to produce a flow of pressurized combustion gases; a turbine disposed aft of the core; a rotatable fan disk mounted forward of the core, the fan disk defining a central aperture and carrying an array of airfoil-shaped fan blades around its periphery, the disk having a forward end and an aft end; and an annular, generally axially-extending forward fan shaft mechanically coupled to the turbine, the forward fan shaft extending through the aperture and coupled to the fan disk for rotation therewith, where the forward fan shaft joins the fan disk at or near the forward end.
  • FIG. 1 schematically depicts a prior art gas turbine engine 10.
  • the engine 10 has a longitudinal axis 11 and includes a fan 12, a low pressure compressor or “booster” 14 and a low pressure turbine (“LPT”) 16 collectively referred to as a "low pressure system”.
  • the LPT 16 drives the fan 12 and booster 14 through an inner shaft 18, also referred to as an "LP shaft”.
  • the engine 10 also includes a high pressure compressor ("HPC”) 20, a combustor 22, and a high pressure turbine (“HPT”) 24, collectively referred to as a "gas generator” or "core".
  • HPC high pressure compressor
  • HPT high pressure turbine
  • core gas generator
  • the high and low pressure systems are operable in a known manner to generate a primary or core flow as well as a fan flow or bypass flow. While the illustrated engine 10 is a high-bypass turbofan engine, the principles described herein are equally applicable to other types of turbine engines.
  • the inner shaft 18 comprises a forward fan shaft 28 and a rear fan shaft 30 coupled together and mounted for rotation in several rolling-element bearings.
  • the forward fan shaft 28 is carried by a first bearing 32 (commonly referred to as a "no. 1 bearing") and a second bearing 34 (commonly referred to as a “no. 2 bearing”).
  • the rear fan shaft 30 is carried by a bearing 36 (commonly referred to as a "#5 bearing").
  • FIG. 2 illustrates a fan 112 and surrounding structure which are constructed according to an aspect of the present invention, and which may be incorporated in the engine 10.
  • the fan 112 comprises a fan disk 138 with a central aperture 139.
  • the fan disk 138 has an annular array of airfoil-shaped fan blades 140 mounted around its periphery.
  • the fan disk 138 has a forward end 142 and an aft end 144.
  • An annular disk arm 150 extends at an angle axially forward and radially inward from the forward end 142 of the disk 138.
  • a forward fan shaft 128 extends between the fan disk 138 and a rear fan shaft 130, and is coupled to the rear fan shaft 130 for rotation therewith, for example by a bolted joint or a splined connection.
  • the forward fan shaft 128 comprises part of a load reduction device.
  • a no. 1 bearing 132 is mounted to a surrounding structural support frame 146 by an annular, generally axially-extending fuse 148.
  • the size, material, and mechanical design of the fuse 148 is selected to fail at a predetermined radial load, such as a load that might occur after separation of a fan blade 140. Failure of the fuse 148 allows the fan disk 138 to rotate about a new axis of rotation without imposing excessive radial loads on the surrounding structure.
  • Other types of fuse structures are known, such as bolted joints or fuse pins designed to fail in tension or in shear, or collapsible member(s) in a frame designed to crush at designated loads. The specific type of fuse structure is not critical to the present invention.
  • the forward fan shaft 128 extends axially forward past the aft end 144 of the fan disk 138, traversing the longitudinal extent of the fan disk 138, and is coupled to the fan disk 138 at a point at or near the forward end 142 of the fan disk 138.
  • the term "coupled to the fan disk at or near the forward end” means that torque is transferred from the forward fan shaft 128 to the fan disk 138 through a load path passing at or through the disk's forward end. It does not necessarily imply any specific type of mechanical connection between the forward fan shaft 128 and the fan disk 138, or require any specific location of a mechanical joint between the two components. In the example shown in FIG.
  • the forward fan shaft 128 includes a tapered aft portion 152. a generally cylindrical axial portion 154. and a flange 156 which extends radially outward from the forward end of the axial portion 154.
  • the flange 156 is coupled to the disk arm 150 for rotation therewith, for example using a bolted or splined connection.
  • the forward fan shaft 128 is substantially less stiff in bending than the prior art design shown in FIG. 1 ).
  • the disk arm 150 shown in FIG. 2 could extend axially forward or aft of the forward end 142 of the fan disk 138.
  • the angle and cross-sectional shape of the disk arm 150 may be varied to provide a bending stiffness suitable for each particular application.
  • the forward fan shaft 128 is shown as being a single integral component, it could be built up from two or more sections joined together, for example using bolted joints.
  • FIG. 3 illustrates an alternative fan 212 and surrounding structure, including a frame 246, fuse 248, and bearing 232 .
  • a forward fan shaft 228 has a tapered aft portion 252 coupled to a rear fan shaft 230 and a generally cylindrical axial portion 254.
  • An annular fan disk 238 carries fan blades 240 and has a forward end 242 and aft end 244.
  • An annular disk arm 250 extends generally axially forward and radially inward from the forward end 242 of the disk 238.
  • the disk arm 250 has a forward portion 256 which extends forward, then curves backward in a "C"-shape, and an aft portion 258 which extends generally axially aft.
  • the aft portion 258 is coupled to the forward fan shaft 228 for rotation therewith, for example with a bolted or splined joint.
  • the additional arc length of the curved portion of the disk arm 250 provides an opportunity to further increase and tune the flexibility of the forward fan shaft 228.
  • the additional curve and arc length could be incorporated into the forward fan shaft 228 instead of the disk arm 250.
  • any of the fan shafts described herein could me made all or partially integral with the fan disk.
  • the forward fan shaft design described herein permits the fan rotor to safely windmill after a blade release event while limiting the bending loads applied to the core. This can be achieved without the need for any specific engine length or bearing position requirements.
EP12165454.5A 2011-04-28 2012-04-25 Moteur à turbine et son dispositif de réduction de charge Withdrawn EP2546460A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/096,645 US20120275921A1 (en) 2011-04-28 2011-04-28 Turbine engine and load reduction device thereof

Publications (2)

Publication Number Publication Date
EP2546460A2 true EP2546460A2 (fr) 2013-01-16
EP2546460A3 EP2546460A3 (fr) 2015-12-23

Family

ID=46084812

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12165454.5A Withdrawn EP2546460A3 (fr) 2011-04-28 2012-04-25 Moteur à turbine et son dispositif de réduction de charge

Country Status (4)

Country Link
US (1) US20120275921A1 (fr)
EP (1) EP2546460A3 (fr)
JP (1) JP2012233474A (fr)
CA (1) CA2775491A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3004227B1 (fr) * 2013-04-09 2016-10-21 Snecma Disque de soufflante pour un turboreacteur
FR3029996B1 (fr) * 2014-12-15 2018-05-04 Safran Helicopter Engines Fusible mecanique frangible par torsion et groupe de refroidissement d'un turbomoteur equipe d'un tel fusible
CN107341316B (zh) * 2017-07-13 2020-07-03 西北工业大学 设计相关压力载荷作用下的结构形状-拓扑联合优化方法
FR3082876B1 (fr) 2018-06-21 2021-01-22 Safran Aircraft Engines Soufflante comprenant une plateforme et un verrou de blocage
FR3089548B1 (fr) 2018-12-07 2021-03-19 Safran Aircraft Engines Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1445107A (en) * 1973-01-12 1976-08-04 Rolls Royce Pitch varying mechanisms for a variable pitch fan
FR2393227A1 (fr) * 1977-05-31 1978-12-29 Snecma Montage d'une machine tournante sur un arbre moteur
DE2745131A1 (de) * 1977-10-07 1979-04-12 Motoren Turbinen Union Kombinationsgasturbinentriebwerk fuer fluggeraete mit v/stol eigenschaften
GB2043833B (en) * 1979-03-17 1982-11-10 Rolls Royce Rotor assembly
GB2080486B (en) * 1980-07-15 1984-02-15 Rolls Royce Shafts
JP2809362B2 (ja) * 1992-03-31 1998-10-08 三菱重工業株式会社 複合ヘリコプタ用動力装置
FR2749883B1 (fr) * 1996-06-13 1998-07-31 Snecma Procede et support de palier permettant de maintenir en fonctionnement un turbomoteur pour aeronef apres apparition d'un balourd accidentel sur un rotor
FR2856430B1 (fr) * 2003-06-20 2005-09-23 Snecma Moteurs Agencement de supports de paliers pour arbre tournant d'un moteur d'aeronef et moteur d'aeronef equipe d'un tel agencement

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
CA2775491A1 (fr) 2012-10-28
EP2546460A3 (fr) 2015-12-23
US20120275921A1 (en) 2012-11-01
JP2012233474A (ja) 2012-11-29

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