WO2013158483A1 - Masselotte d'équilibrage à ressort arrêté et ensemble rotor - Google Patents

Masselotte d'équilibrage à ressort arrêté et ensemble rotor Download PDF

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Publication number
WO2013158483A1
WO2013158483A1 PCT/US2013/036328 US2013036328W WO2013158483A1 WO 2013158483 A1 WO2013158483 A1 WO 2013158483A1 US 2013036328 W US2013036328 W US 2013036328W WO 2013158483 A1 WO2013158483 A1 WO 2013158483A1
Authority
WO
WIPO (PCT)
Prior art keywords
balance weight
spring arms
centerbody
turbine rotor
distal end
Prior art date
Application number
PCT/US2013/036328
Other languages
English (en)
Inventor
Nathan Tyler WOODS
Aaron Todd Williams
Robert Patrick Tameo
Michael Thomas
Charles Eric Lavender
Original Assignee
General Electric Company
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 US13/452,154 external-priority patent/US9297258B2/en
Application filed by General Electric Company filed Critical General Electric Company
Priority to CA2870267A priority Critical patent/CA2870267A1/fr
Priority to EP13718728.2A priority patent/EP2839114A1/fr
Priority to CN201380020883.6A priority patent/CN104285035B/zh
Priority to JP2015504777A priority patent/JP6027224B2/ja
Publication of WO2013158483A1 publication Critical patent/WO2013158483A1/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
    • 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
    • F01D5/027—Arrangements for balancing

Definitions

  • This invention relates generally to rotating machinery and more particularly to apparatus for balancing rotors.
  • Gas turbine engines typically include several rotor stages, each having a rotor disk carrying an array of airfoils, i.e., compressor or turbine blades.
  • Turbine rotors must be balanced to prevent damage and excessive loads on bearings and supporting structures, as well as efficiency losses caused by loss of clearance between the airfoils and the surrounding structure (caused by, e.g., shroud rubs).
  • balance weights that can be re-positioned to redistribute the mass of the rotor as needed and allow the system unbalance to be fine-tuned to meet precise requirements.
  • Separable balance weights are a common practice in larger gas turbine engines. These include bolts, washers, nuts and other fasteners of varying sizes.
  • CUR VIC couplings and friction joints are assembled using a single bolt or a group of bolts (referred to as a "tie rod” or “tie bolts”) spanning the length of the assembly.
  • a tie bolt configuration weighs less than a conventional bolted joint, but the absence of bolt holes eliminates convenient features on the rotor disk which could otherwise be used to attach separable balance weights.
  • the current state of the art for smaller turbine engines is to balance the assembly by selectively machining a sacrificial surface on the rotating part. Material is removed at the location of peak unbalance to redistribute the mass of the rotor about the axis of rotation. This process is irreversible and risks damaging a component such as an integrally-bladed rotor or "blisk", which is both safety-critical and expensive.
  • a balance weight for a turbine rotor includes: a block- like centerbody pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; at least one locating structure extending from a radially outer surface of the balance weight; and a limit tab extending radially inward from a distal end of each of the spring arms.
  • a turbine rotor assembly includes: a rotor element including an annular hub surface and an annular flange surrounding the hub surface, spaced away from the hub surface so as to define a pocket; and at least one balance weight disposed in the pocket, including: a block-like centerbody; a pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; at least one locating feature extending radially outward from the balance weight; and a limit tab extending radially inward from a distal end of each of the spring arms; wherein the spring arms and the centerbody resiliently bear against the flange and the hub surface, respectively, so as to retain the balance weight in the pocket.
  • a radial height of the limit tabs is selected so as to prevent insertion of the balance weight into the pocket if the spring arms are deflected beyond a predetermined limit.
  • Figure 1 is a cross-sectional view of a gas turbine engine constructed in accordance with an aspect of the present invention
  • Figure 2 is an enlarged view of the forward portion of the compressor of the engine shown in Figure 1 ;
  • Figure 3 is an enlarged view of the aft portion of the compressor of the engine shown in Figure 1 ;
  • Figure 4 is a perspective view of a balance weight constructed according to an aspect of the present invention.
  • Figure 5 is a rear elevational view of the balance weight of Figure 4.
  • Figure 6 is a perspective view of the balance weight of Figure 4 installed in a rotor disk of the engine of Figure 1 ;
  • Figure 7 is a front view of a spanner tool for use with a balance weight
  • Figure 8 is a side view of the spanner tool of Figure 7;
  • Figure 9 is a rear view of the spanner tool of Figure 7;
  • Figure 10 is a view of the spanner tool of Figure 7 in use
  • Figure 11 is a perspective view of a balance weight constructed according to another aspect of the present invention.
  • Figure 12 is a rear elevational view of the balance weight of Figure 11;
  • Figure 13 is a perspective view of the balance weight of Figure 11 installed in the engine of Figure 1;
  • Figure 14 is a cross-sectional view of portion of a compressor of a gas turbine engine, with a balance weight installed therein;
  • Figure 15 is a perspective view of the balance weight of Figure 14;
  • Figure 16 is a rear elevational view of the balance weight of Figure 15.
  • Figure 17 is a perspective view of the balance weight of Figure 15 in an installed condition.
  • Figure 1 depicts an exemplary gas turbine engine 10 having a compressor 12, a combustor 14, a high pressure or gas generator turbine 16, and a work turbine 18, all arranged in a serial flow relationship.
  • the compressor 12 provides compressed air that passes into the combustor 14 where fuel is introduced and burned, generating hot combustion gases.
  • the hot combustion gases are discharged to the gas generator turbine 16 where they are expanded to extract energy therefrom.
  • the gas generator turbine 16 drives the compressor 12 through an impeller shaft 20. Pressurized air exiting from the gas generator turbine 16 is discharged to the work turbine 18 where it is further expanded to extract energy.
  • the work turbine 18 drives an inner shaft 22.
  • the engine is a turboshaft engine, and the inner shaft 22 would be coupled to an external load such as a reduction gearbox or propeller.
  • an external load such as a reduction gearbox or propeller.
  • turboprop, turbojet, and turbofan engines as well as turbine engines used for other vehicles or in stationary applications.
  • turbine engines used for other vehicles or in stationary applications.
  • rotating machinery e.g. wheels, gears, shafts, etc.
  • the compressor 12 includes five axial-flow rotor stages and one mixed-flow stage which is positioned immediately upstream of the combustor 14.
  • the first stage rotor 24 of the compressor 12 is an integrally-b laded rotor or "blisk" in which a rotor disk 26 and a plurality of airfoil-shaped compressor blades 28 are formed as one integral component.
  • the aft end of the rotor disk 26 includes an annular hub surface 30 and an annular flange 32 extending over the hub surface 30. Together, the hub surface 30 and the flange 32 define a pocket 34 (best seen in Figure 6).
  • the final stage of the compressor 12 includes a rotor disk 40 which carries a plurality of blades 42.
  • the annular impeller shaft 20 extends axially aft from the rotor disk 40.
  • the intermediate section of the impeller shaft 20 includes an annular hub surface 46 and an annular flange 48 extending over the hub surface 46. Together, the hub surface 46 and the flange 48 define a pocket 50 (best seen in Figure 13).
  • the flange 48 includes an annular array of apertures formed therein. In the illustrated example, as seen in Figure 13, this array comprises open-ended slots 52 alternating with holes 54.
  • One or more forward balance weights 60 are installed in the pocket 34 of the first stage rotor 24, and one or more aft balance weights 160 are installed in the pocket 50 of the impeller shaft 20.
  • the exact number, position, and distribution of weights will vary by individual engine. In the particular engine illustrated, only two balance weights are used. Correction of rotor imbalance is accomplished by re-positioning the weights as needed.
  • Figures 4 and 5 illustrate one of the forward balance weights 60 in more detail. It is generally arcuate in shape and comprises a block-like centerbody 62 with resilient spring arms 64 extending laterally outward therefrom. A notch 66 is formed in the radially inner end of the centerbody 62. At the distal end of each spring arm 64, an axially-elongated rail 68 extends radially outward. Opposite each rail 68, a stop block 70 extends radially inward.
  • the forward balance weights 60 may be constructed from any material with an appropriate density and the ability to form the spring arms which can deflect elastically. For example, metal alloys may be used.
  • the forward balance weights 60 are installed into the first stage rotor 24 as follows.
  • the spring arms 64 are deflected radially inward relative to the centerbody 62. They may be held in this position by an appropriate tool or jig. Then the forward balance weight 60 is slid axially into the pocket 34, at the appropriate position. The spring arms 64 are then released. After release, the residual spring force urges the spring arms 64 radially outward against the flange 32 and urges the centerbody 62 against the hub surface 30.
  • the rails 68 engage the grooves 38 in the inner surface of the flange 32 to prevent tangential movement.
  • a mating component in this case the forward end of an annular shaft 72, seen in Figure 2 abuts the notch 66 to prevent axial movement of the forward balance weight 60.
  • Figure 6 shows one of the forward balance weights 60 in an installed condition. During engine operation, centrifugal loading reseats the forward balance weights 60 against the flange 32.
  • the forward balance weights 60 can be repositioned circumferentially while the compressor 12 is assembled, for example through use of a spanner-wrench tool.
  • Figures 7-9 illustrate a suitable tool 74 which has an elongated handle 76 and a curved head 78 with spanner fingers 80 extending radially inward and laterally outward from its distal ends. As shown in Figure 10, the tool 74 is inserted into the pocket 34 and used to deflect the spring arms 64 radially inward, disengaging the rails 68 from the grooves 38.
  • the tool 74 may then be moved tangentially in the direction of the arrows, causing the spanner fingers 80 to contact the forward balance weight 60 and push it to a new position. Once the tool 74 is removed, the rails 68 re-engage grooves 38 at the new location. During this operation, the stop blocks 70 contact the annular shaft 72 if an attempt is made to deflect the spring arms 64 too far. This prevents permanent deformation of the spring arms 64.
  • Figures 11 and 12 illustrate one of the aft balance weights 160 in more detail. It is generally arcuate in shape and comprises a block-like centerbody 162 with resilient spring arms 164 extending laterally outward therefrom. An anti-rotation lug 166 extends radially outward from the centerbody 162. At the distal end of each spring arm 164, a shear pin 168 extends radially outward. Opposite each shear pin 168, a stop block 170 extends radially inward. A forward face 172 of the aft balance weight 160 has a convex contour complementary to the cross-sectional profile of the pocket 50 in the impeller shaft 20.
  • the aft balance weights 160 may be constructed from any material with an appropriate density and the ability to form the spring arms which can deflect elastically. For example, metal alloys may be used.
  • the aft balance weights 160 are installed using a method similar to that for the forward balance weights 60, as follows.
  • the spring arms 164 are deflected radially inward relative to the centerbody 162, as shown by the arrows in Figure 12. They may be held in this position by an appropriate tool or jig. Then the aft balance weight 160 is slid axially into the pocket 50, at the appropriate position.
  • the stop blocks 170 are sized and shaped so as to prevent insertion into the pocket 50 if the spring arms 164 are deflected too far, and thus prevent permanent deformation of the spring arms 164. The spring arms 164 are then released.
  • FIG. 13 shows one of the aft balance weights 160 in an installed condition. During engine operation, centrifugal loading reseats the aft balance weights 160 against the flange 48. If necessary, the aft balance weights 160 can be removed and re-positioned while the compressor rotor is assembled, without any unique jigs or tools.
  • balance weights 60 and 160 have described as “forward” and “aft” weights, it will be understood that these terms are used merely for convenience in description of a particular embodiment. Depending upon the specific engine application and the mating hardware, either design could be used on the forward or aft face of a turbine rotor disk or shaft. Furthermore, the anti-rotation and axial restraint features could be modified or used in different combinations to produce a balance weight suitable for a particular application.
  • Figure 14 illustrates a portion of a compressor section of a gas turbine engine, similar in operating principle to the engine 10 described above.
  • a first stage rotor 224 in the compressor section is an integrally-bladed rotor or "blisk" in which a rotor disk 226 and a plurality of airfoil-shaped compressor blades 228 are formed as one integral component.
  • the aft end of the rotor disk 226 includes an annular hub surface 230 and an annular flange 232 extending over the hub surface 230. Together, the hub surface 230 and the flange 232 define a pocket 234 (best seen in Figure 17).
  • An inner surface 236 of the flange 232 has an array of grooves 238 formed therein (again, see Figure 17).
  • One or more balance weights 260 are installed in the pocket 234 of the first stage rotor 224. The exact number, position, and distribution of weights will vary by individual engine. Correction of rotor imbalance is accomplished by re-positioning the weights as needed.
  • Figures 15 and 16 illustrate one of the balance weights 260 in more detail. It is generally arcuate in shape and comprises a block-like centerbody 262 with resilient spring arms 264 extending laterally outward therefrom. A notch 266 is formed in the radially inner end of the centerbody 262. At the distal end of each spring arm 264, an axially-elongated rail 268 extends radially outward. Opposite each rail 268, a stop block 270 extends radially inward. A limit tab 271 extends radially inward from each stop block 270.
  • the balance weights 260 may be constructed from any material with an appropriate density and the ability to form the spring arms which can deflect elastically. For example, metal alloys may be used.
  • the balance weights 260 are installed into the first stage rotor 224 as follows.
  • the spring arms 264 are deflected radially inward relative to the centerbody 262. They may be held in this position by an appropriate tool or jig. Then the balance weight 260 is slid axially into the pocket 234, at the appropriate position.
  • the radial height "FT of each limit tab 271 relative to the stop block 270 is selected to prevent deflection of the spring arms 264 beyond a predetermined limit. More specifically, the height H is set such that the limit tab 271 will interfere with the hub surface 230 before the spring arm 264 can be deflected enough to cause plastic deformation thereof. After insertion, the spring arms 264 are released.
  • FIG. 17 shows one of the balance weights 260 in an installed condition. During engine operation, centrifugal loading reseats the forward balance weights 260 against the flange 232.
  • the balance weights 260 may be repositioned as described above for the balance weights 60 and 160. It is also noted that the limit tab feature described with respect to the balance weights 260 may be incorporated in the balance weights 60 or 160.
  • the balance weight design described herein has several advantages over the current state-of-the-art for small engines. Process control is improved compared to material removal directly from the first stage rotor 24, which introduces local stress concentrations on highly stressed critical rotating parts. Any stress concentration features present on the balance weights 60, 160, or 260 would be generated using precision machining techniques and are therefore more well controlled. Engine cleanliness is also enhanced, as the balance weights do not require any machining at engine assembly and therefore do not create dust or grit that could contaminate the engine system. Finally, cycle time for the balancing process is reduced, because the balance weights can be easily re-positioned while the rotor is loaded in a balance machine, eliminating the rework loop associated with a material removal balancing process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention porte sur une masselotte d'équilibrage pour un rotor de turbine, qui comprend : un corps central du type bloc (62) ; une paire de bras à ressort élastiques (64) qui s'étendent latéralement des côtés opposés du corps central, le corps central et les bras à ressort définissant collectivement une forme arquée ; au moins une structure de positionnement s'étendant d'une surface radialement extérieure de la masselotte d'équilibrage ; et une patte limite (170, 271) s'étendant radialement vers l'intérieur d'une extrémité distale de chacun des bras à ressort.
PCT/US2013/036328 2012-04-20 2013-04-12 Masselotte d'équilibrage à ressort arrêté et ensemble rotor WO2013158483A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
CA2870267A CA2870267A1 (fr) 2012-04-20 2013-04-12 Masselotte d'equilibrage a ressort arrete et ensemble rotor
EP13718728.2A EP2839114A1 (fr) 2012-04-20 2013-04-12 Masselotte d'équilibrage à ressort arrêté et ensemble rotor
CN201380020883.6A CN104285035B (zh) 2012-04-20 2013-04-12 涡轮转子组件和用于涡轮转子的平衡配重
JP2015504777A JP6027224B2 (ja) 2012-04-20 2013-04-12 トラップ式バランスウェイトおよびロータ組立体

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/452,154 2012-04-20
US13/452,154 US9297258B2 (en) 2009-06-16 2012-04-20 Trapped spring balance weight and rotor assembly

Publications (1)

Publication Number Publication Date
WO2013158483A1 true WO2013158483A1 (fr) 2013-10-24

Family

ID=48184508

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/036328 WO2013158483A1 (fr) 2012-04-20 2013-04-12 Masselotte d'équilibrage à ressort arrêté et ensemble rotor

Country Status (5)

Country Link
EP (1) EP2839114A1 (fr)
JP (1) JP6027224B2 (fr)
CN (1) CN104285035B (fr)
CA (1) CA2870267A1 (fr)
WO (1) WO2013158483A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4036372A1 (fr) * 2021-02-02 2022-08-03 Pratt & Whitney Canada Corp. Ensemble d'équilibrage de rotor

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101891921B1 (ko) * 2017-05-30 2018-09-28 두산중공업 주식회사 터빈 장치의 블레이드 진동 측정 장치
CN109630205B (zh) * 2018-12-11 2021-08-03 中国航发四川燃气涡轮研究院 一种自锁紧的平衡配重结构
US11732585B2 (en) * 2021-01-28 2023-08-22 General Electric Company Trapped rotatable weights to improve rotor balance

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1416040A (fr) * 1963-11-13 1965-10-29 B M W Triebwerkbau Ges M B H Procédé pour la fixation d'une masse d'équilibrage sur un corps tournant notamment sur les rotors de machines tournant à grande vitesse, les masses obtenues par la mise en oeuvre du procédé précédent ou similaire ainsi que les corps tournants pourvus de ces masses
US4817455A (en) * 1987-10-15 1989-04-04 United Technologies Corporation Gas turbine engine balancing
US20100316496A1 (en) * 2009-06-16 2010-12-16 General Electric Company Trapped spring balance weight and rotor assembly

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US4294135A (en) * 1979-01-12 1981-10-13 The United States Of America As Represented By The Secretary Of The Navy Turbomachine balance correction system
FR2716931B1 (fr) * 1994-03-03 1996-04-05 Snecma Système d'équilibrage et d'amortissement d'un dique de turbomachine.
FR2868807B1 (fr) * 2004-04-09 2008-12-05 Snecma Moteurs Sa Dispositif d'equilibrage d'une piece en rotation en particulier d'un rotor de turboreacteur
US20050265846A1 (en) * 2004-06-01 2005-12-01 Przytulski James C Balance assembly for rotary turbine component and method for installing and/or adjusting balance weight
US8186954B2 (en) * 2008-09-30 2012-05-29 General Electric Company Gas turbine engine rotor and balance weight therefor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1416040A (fr) * 1963-11-13 1965-10-29 B M W Triebwerkbau Ges M B H Procédé pour la fixation d'une masse d'équilibrage sur un corps tournant notamment sur les rotors de machines tournant à grande vitesse, les masses obtenues par la mise en oeuvre du procédé précédent ou similaire ainsi que les corps tournants pourvus de ces masses
US4817455A (en) * 1987-10-15 1989-04-04 United Technologies Corporation Gas turbine engine balancing
US20100316496A1 (en) * 2009-06-16 2010-12-16 General Electric Company Trapped spring balance weight and rotor assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4036372A1 (fr) * 2021-02-02 2022-08-03 Pratt & Whitney Canada Corp. Ensemble d'équilibrage de rotor
US11578599B2 (en) 2021-02-02 2023-02-14 Pratt & Whitney Canada Corp. Rotor balance assembly

Also Published As

Publication number Publication date
EP2839114A1 (fr) 2015-02-25
CA2870267A1 (fr) 2013-10-24
CN104285035A (zh) 2015-01-14
JP6027224B2 (ja) 2016-11-16
JP2015515576A (ja) 2015-05-28
CN104285035B (zh) 2017-03-01

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