WO2014176178A1 - Compartiment de palier à conduites de fluide intégrées - Google Patents

Compartiment de palier à conduites de fluide intégrées Download PDF

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Publication number
WO2014176178A1
WO2014176178A1 PCT/US2014/034843 US2014034843W WO2014176178A1 WO 2014176178 A1 WO2014176178 A1 WO 2014176178A1 US 2014034843 W US2014034843 W US 2014034843W WO 2014176178 A1 WO2014176178 A1 WO 2014176178A1
Authority
WO
WIPO (PCT)
Prior art keywords
wall
bearing
integral
bearing compartment
fluid supply
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.)
Ceased
Application number
PCT/US2014/034843
Other languages
English (en)
Inventor
David R. Olsen
Frederic G. MINER
Paul H. DOLMAN
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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Priority to EP14787796.3A priority Critical patent/EP2989299A4/fr
Priority to US14/785,094 priority patent/US20160069211A1/en
Publication of WO2014176178A1 publication Critical patent/WO2014176178A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • 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
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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

Definitions

  • the described subject matter relates generally to ground-based turbine engines and more specifically to fluid systems for turbine bearings.
  • Industrial gas turbine engines, and other gas turbine engines utilize a power turbine or an alternate means for rotatably driving a power conversion device.
  • Lubrication and air supply lines for the power turbine shaft bearings are typically mounted externally along the bearing compartment and the rest of the power turbine assembly. While this makes the supply lines accessible, external mounting subjects the large diameter lines to damage during delivery and during other maintenance tasks.
  • a turbine module comprises a turbine shaft, a rotor assembly secured to the shaft, a bearing assembly rotatably supporting the turbine shaft, a bearing housing containing the bearing assembly, and a bearing compartment containing the bearing housing.
  • the bearing compartment includes a wall having at least one integral fluid supply passage in fluid communication with the bearing housing. The at least one integral fluid passage extends generally longitudinally through the bearing compartment wall.
  • a turbomachine bearing compartment comprises a first wall section, a fluid supply inlet disposed proximate a first wall end surface, a fluid supply outlet formed through a first wall inner surface; and a first integral passage segment incorporated into the first wall section between first inner and outer wall surfaces.
  • the first integral passage segment extends generally longitudinally through at least a portion of the first wall section and provides communication between the fluid supply inlet and the fluid supply outlet.
  • FIG. 1 depicts an example industrial gas turbine engine.
  • FIG. 2 shows a detailed cross-section of a power turbine section.
  • FIG. 3 is a detailed sectional view of an example power turbine bearing compartment.
  • FIG. 4 shows a forward facing radial cross-section of the power turbine bearing compartment housing including integrated longitudinal fluid supply lines.
  • FIG. 1 is a simplified partial cross-sectional view of gas turbine engine 10, comprising inlet 12, compressor 14 (with low pressure compressor 16 and high pressure compressor 18), combustor 20, engine turbine 22 (with high pressure turbine 24 and low pressure turbine 26), turbine exhaust case 28, power turbine module 30, low pressure shaft 32, high pressure shaft 34, and power shaft 36.
  • Gas turbine engine 10 can, for instance, be an industrial power turbine.
  • Low pressure shaft 32, high pressure shaft 34, and power shaft 36 are situated along rotational axis A.
  • low pressure shaft 32 and high pressure shaft 34 are arranged concentrically, while power shaft 36 is disposed axially aft of low pressure shaft 32 and high pressure shaft 34.
  • Low pressure shaft 32 defines a low pressure spool including low pressure compressor 16 and low pressure turbine 26.
  • High pressure shaft 34 analogously defines a high pressure spool including high pressure compressor 18 and high pressure turbine 24.
  • airflow F is received at inlet 12, is pressurized by low pressure compressor 16 and high pressure compressor 18. Fuel is injected at combustor 20, where the resulting fuel-air mixture is ignited.
  • Expanding combustion gasses rotate high pressure turbine 24 and low pressure turbine 26, thereby driving high and low pressure compressors 18 and 16 through high pressure shaft 34 and low pressure shaft 32, respectively.
  • compressor 14 and engine turbine 22 are depicted as two-spool components with high and low sections on separate shafts, single spool or 3+ spool embodiments of compressor 14 and engine turbine 22 are also possible.
  • Turbine exhaust case 28 carries airflow from low pressure turbine 26 to power turbine module 30, where this airflow drives power shaft 36.
  • Power shaft 36 can, for instance, drive an electrical generator, pump, mechanical gearbox, or other accessory (not shown).
  • FIG. 2 shows a detailed cross-section of power turbine module 30 and also includes turbine shaft 36, rotor assembly 38, airfoils 42, rotor disks 44, shaft forward end 46A, shaft aft end 46B, power turbine exhaust case (PTEC) 48, bearing housing 50, bearing compartment 52, fluid supply passages 54, bearing compartment wall 56, main bearing assembly 58, secondary bearing assemblies 60, exit duct 62, and return 64.
  • PTEC power turbine exhaust case
  • the turbine module shown in FIG. 2 is described with reference to an example power turbine module such as power turbine module 30 of the example industrial gas turbine engine 10 shown in FIG. 1.
  • an example power turbine module such as power turbine module 30 of the example industrial gas turbine engine 10 shown in FIG. 1.
  • various embodiments of a turbine module and its associated components can be adapted to other turbine sections of gas turbine engine 10, such as high pressure turbine 24 and low pressure turbine 26.
  • embodiments of a turbine module and associated components can be adapted to turbine sections of other gas and steam turbine engines.
  • the example power turbine module 30 includes turbine shaft 36 rotatable about center line, or axis A.
  • Rotor assembly 38 is secured to power turbine shaft 36.
  • rotor assembly 38 includes several rotor stages each including a plurality of airfoils 42 circumferentially distributed around each rotor disk 44.
  • Working gas C is directed through power turbine module 30 to rotate rotor assembly 38, which drives power turbine shaft 36 from shaft forward end 46A.
  • Working gas C is exhausted out from power turbine exhaust case (PTEC) 48.
  • Power turbine shaft 36 is rotatably supported aft of rotor assembly 38 by one or more power turbine bearing assemblies retained in bearing housing 50.
  • One or more pieces of industrial equipment such as an electrical generator or mechanical pump (not shown) can be secured to shaft aft end 46B to be driven by power turbine module 30.
  • FIG. 2 also shows bearing housing 50 secured in bearing compartment 52.
  • one or more fluid supply passages 54 can be incorporated into various portions of bearing compartment wall 56 to be in fluid communication with one or more axially spaced apart bearing assemblies disposed within bearing housing 50.
  • Main bearing assembly 58 and secondary bearing assemblies 60 are axially spaced apart along the length of bearing compartment 58.
  • Lubricant is communicated from fluid supply passages 54 to each bearing assembly 58, 60. Used lubricant is flung outward by the bearings toward bearing housing 50, where it is collected and returned to the engine oil system through exit duct 62 and return line 64.
  • integral passages 54 can include or more integral passage segments formed longitudinally within bearing compartment wall 56. Fluid lines, often carrying lubricant, air, and other fluids for a turbine module, are usually separately mounted primarily on the outside of the bearing compartment. While this makes the supply lines accessible, it also subjects these lines to environmental damage during transport and during unrelated maintenance tasks.
  • integral passages 54 simplify more complicated repair and maintenance tasks on the turbine module (e.g., power turbine module 30) by reducing steps required to protect (or remove and reinstall) individual external fluid lines. In larger installations, it is typical for workers to climb onto and over the turbine case in order to access certain components.
  • FIG. 3 shows a more detailed view of example bearing compartment 52 for power turbine module 30 having one or more integral fluid supply passages 54 incorporated into bearing compartment wall 56.
  • FIG. 3 also includes exit duct 62, return line 64, forward wall section 66A, aft wall section 66B, transition wall section 68, shaft passage 70, forward bearing compartment inner surface 72A, aft bearing compartment inner surface 72B, forward bearing compartment outer wall surface 74 A, aft bearing compartment outer wall surface 74B, lubricant supply outlets 76, main bearing housing portion 78A, secondary bearing housing portions 78B, forward integral fluid passage segment 80A, aft integral fluid passage segment 80B, passage inlets 82A, 82B, mounting surface 84, transition passage 86, supply pipes 88, fitting 90, plug 91, bearing compartment end walls 92A, 92B, and drain 93.
  • Power turbine shaft 36 (shown in FIG. 2) is omitted for clarity.
  • bearing compartment wall 56 includes forward wall section 66A and aft wall section 66B connected by transition wall section 68.
  • Wall 56 can additionally or alternatively be divided into upper and lower halves (shown in FIG. 4) so that each half of bearing compartment outer wall 56 can be sand cast into a general U- shape or crescent shape. This defines the rough shape of shaft passage 70.
  • Each half can be further machined so that bearing housing(s) 50 generally conform to forward bearing compartment inner surface 72A, and aft bearing compartment inner surface 72B.
  • Forward wall section 66A can be defined relative to forward inner wall surface 72A and forward outer wall surface 74A.
  • Aft wall section 66B can be similarly defined relative to aft inner wall surface 72B and aft outer wall surface 74B.
  • Fluid supply passages 54 provide lubricant to main bearing assembly 60 and secondary bearing assemblies 62 (shown in FIG. 2) via one or more lubricant supply outlets 76 in communication with bearing housing(s) 50.
  • axially spaced apart supply outlets 76 are disposed axially along an upper half of bearing housing 50 proximate main bearing housing portion 78A and secondary bearing housing portions 78B.
  • Each integral fluid supply passage 54 can include one or more segments formed in different sections of wall 56.
  • fluid supply passage 54 includes forward integral fluid passage segment 80A incorporated into forward wall section 66A, and aft integral fluid passage segment 80B incorporated into aft outer wall section 66B.
  • aft integral passage segment 80B is longitudinally spaced apart from and/or circumferentially aligned with forward integral passage segment 80A. Spacing may depend, for example, on the relative nominal diameters of forward and aft wall sections 66A, 66B.
  • forward integral fluid passage segment 80 A can be formed into bearing compartment wall 56, e.g., by gun drilling longitudinally through forward wall section 66A from forward passage inlet 82A.
  • FIG. 3 also shows optional aft integral fluid passage segment 80B, which also can be formed into bearing compartment wall 56, e.g., by gun drilling longitudinally through aft wall section 66B from aft passage inlet 82B.
  • forward wall section 66A has a smaller nominal diameter than aft wall section 66B to permit interconnection of power turbine module 30 to an adjacent turbine module (e.g., turbine exhaust case 28 and/or low pressure turbine 26 shown in FIG. 1).
  • wall transition section 68 can comprise flange or mounting surface 84 as shown in FIG. 3. Though shown with conventional bolt-type fasteners, this interconnection can additionally or alternatively include other modes of securing the two modules such as interference fittings.
  • transition wall section 68 can be stepped or tapered.
  • integral transition passage 86 Forward and aft integral passage segments 80A, 80B can be interconnected by integral transition passage 86 to form a single effective integral passage 54. As shown in FIG. 3, integral transition passage 86 can be drilled at an angle from shaft passage 70 and forward wall inner surface 72A. This results in an angled fluid supply outlet 76.
  • fluid can be received via forward passage inlet 82A and/or aft passage inlet
  • supply pipes 88 which may be lubricant and/or buffer air supply lines, are engaged with suitable fluid-tight fitting(s) 90 metallurgically bonded to one or both bearing compartment end wall(s) 92 A, 92B.
  • Plug 91 can also be inserted into forward or aft passage inlet 82A, 82B so as to maintain fluid pressure in the single effective integral passage 54 and prevent leakage.
  • forward and aft integral fluid passage segments 80A, 80B operate as separate integral passages 54.
  • Received fluid can be communicated along forward integral fluid passage segment 80A to one or more of axially spaced apart main bearing assembly 58 and secondary bearing assemblies 60.
  • Corresponding axially spaced apart fluid supply outlet(s) 76 respectively provide fluid communication between integral fluid passage segment(s) 80A, 80B, and the one or more bearing assemblies 58, 60.
  • used lubricant can collect in drains 93, and exit through duct 62 into return line 64.
  • FIG. 4 is a sectional view taken through main bearing assembly 60 (across line 4-
  • bearing compartment wall 56 is divided into upper and lower halves 94A, 94B which may be separately cast and fastened with bearing housing 50 retained therein.
  • Lubricant passage 95A is disposed above main bearing assembly 58 to supply fresh lubricant, while buffer air passage 95B is disposed through another portion of bearing compartment 52 and circumferentially spaced apart from lubricant passage 95 A.
  • One or more gutters 96 are recessed into inner surface 97 of main bearing housing portion 78A, which passes the used lubricant toward drain 93 and into exit duct 62 and return line 64 (shown in FIG. 3). Gutter 96 can partially or completely circumscribe each bearing assembly (e.g., main bearing assembly 64). Additionally or alternatively gutter(s) 96 can be provided for secondary bearing assemblies 66 (shown in FIGS. 2 and 3).
  • power turbine module 30 is one example turbine module for a large-scale gas turbine engine.
  • Many such ground-based engines have a large nominal diameter to operate large-scale electrical machines or transport pumps.
  • the entirety of the forward and/or aft wall sections each have a cross- sectional outer diameter measuring more than about 1.0 m (about 39 inches).
  • passage segments 88A, 88B can have a first longitudinal dimension along the forward wall segment, and a first cross-sectional diameter, a ratio of the first longitudinal dimension to the first cross-sectional diameter measuring at least about 10.
  • the first cross-sectional passage diameter measures at least about 30 mm (about 1.2 inches). Larger embodiments have first cross-sectional passage diameter measuring at least about 75 mm (about 3.0 inches).
  • a turbine module comprises a turbine shaft, a rotor assembly secured to the shaft, a bearing assembly rotatably supporting the turbine shaft, a bearing housing containing the bearing assembly, and a bearing compartment containing the bearing housing.
  • the bearing compartment includes a wall having at least one integral fluid supply passage in fluid communication with the bearing housing. The at least one integral fluid passage extends generally longitudinally through the bearing compartment wall.
  • the apparatus of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
  • a further embodiment of the foregoing turbine module further comprising a plurality of axially spaced apart bearing assemblies, and a plurality of axially spaced apart fluid supply outlets in respective fluid communication with the bearing housing proximate each of the plurality of bearing assemblies.
  • bearing compartment comprises a first cylindrical or frustoconical wall section, and a second cylindrical or frustoconical wall section longitudinally adjacent to the first wall section.
  • the bearing compartment further comprises a wall transition section connecting the first wall portion to the second wall portion, wherein the wall transition section includes at least one mounting surface for interconnecting the turbine module to a longitudinally adjacent module.
  • the fluid supply passage comprises a first integral passage segment extending generally longitudinally through at least a portion of the first wall section, a second integral passage segment extending generally longitudinally through at least a portion of the second wall section, and a transition passage segment disposed in the wall transition section interconnecting the first and second integral passage segments.
  • bearing compartment wall includes a plurality of circumferentially spaced apart integral fluid supply passages, each of the plurality of fluid supply passages including at least one passage segment extending generally longitudinally through at least a portion of a cylindrical or frustoconical wall section.
  • a turbomachine bearing compartment comprises a first wall section, a fluid supply inlet disposed proximate a first wall end surface, a fluid supply outlet formed through a first wall inner surface; and a first integral passage segment incorporated into the first wall section between first inner and outer wall surfaces.
  • the first integral passage segment extends generally longitudinally through at least a portion of the first wall section and provides communication between the fluid supply inlet and the fluid supply outlet.
  • the apparatus of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional components:
  • a further embodiment of the foregoing bearing compartment further comprising a plurality of axially spaced apart fluid supply outlets in communication with the first integral fluid supply passage.
  • a further embodiment of any of the foregoing bearing compartments further comprising a wall transition section connecting the first wall portion to the second wall portion.
  • a further embodiment of any of the foregoing bearing compartments further comprising a second integral passage segment incorporated into the second wall section and extending generally longitudinally through at least a portion of the second wall section between second radially inner and outer wall surfaces.
  • a further embodiment of any of the foregoing bearing compartments further comprising a transition passage segment interconnecting the first and second integral passage segments to define a contiguous integral fluid supply passage.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Abstract

L'invention concerne un module de turbine comprenant un arbre de turbine, un ensemble rotor fixé à l'arbre, un ensemble palier supportant en rotation l'arbre de turbine, un logement de palier contenant l'ensemble palier et un compartiment de palier contenant le logement de palier. Une paroi de compartiment de palier comprend au moins un passage d'alimentation en fluide formé d'un seul bloc en communication fluidique avec le logement de palier. Le(s) passage(s) de fluide formé(s) d'un seul bloc s'étend(ent) généralement longitudinalement à travers la paroi de compartiment de palier.
PCT/US2014/034843 2013-04-22 2014-04-21 Compartiment de palier à conduites de fluide intégrées Ceased WO2014176178A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14787796.3A EP2989299A4 (fr) 2013-04-22 2014-04-21 Compartiment de palier à conduites de fluide intégrées
US14/785,094 US20160069211A1 (en) 2013-04-22 2014-04-21 Bearing compartment with integrated fluid lines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361814708P 2013-04-22 2013-04-22
US61/814,708 2013-04-22

Publications (1)

Publication Number Publication Date
WO2014176178A1 true WO2014176178A1 (fr) 2014-10-30

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PCT/US2014/034843 Ceased WO2014176178A1 (fr) 2013-04-22 2014-04-21 Compartiment de palier à conduites de fluide intégrées

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US (1) US20160069211A1 (fr)
EP (1) EP2989299A4 (fr)
WO (1) WO2014176178A1 (fr)

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IT201800006394A1 (it) * 2018-06-18 2019-12-18 Sistema di spurgo per cassa cuscino

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Publication number Priority date Publication date Assignee Title
IT202100003647A1 (it) * 2021-02-17 2022-08-17 Nuovo Pignone Tecnologie Srl Serbatoio di contenimento di allagamento
US20250250934A1 (en) * 2024-02-06 2025-08-07 Rtx Corporation Alternate lubrication mechanisms for vehicle bearings lubricant dispenser

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US4086759A (en) * 1976-10-01 1978-05-02 Caterpillar Tractor Co. Gas turbine shaft and bearing assembly
JP2816583B2 (ja) * 1989-11-22 1998-10-27 ヤンマーディーゼル株式会社 ２軸式非常用ガスタービン
US20030059295A1 (en) * 2001-09-26 2003-03-27 Olsen Andrew J. Interchangeable power turbine cartridge assembly
US20100111691A1 (en) * 2008-11-06 2010-05-06 Honeywell International Inc. Turbine engine components
US20110305572A1 (en) * 2009-03-24 2011-12-15 Rolls-Royce Plc Mechanical arrangement

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US7568843B2 (en) * 2006-08-25 2009-08-04 Pratt & Whitney Canada Corp. Oil bearing and tube assembly concept
US8210316B2 (en) * 2006-12-12 2012-07-03 United Technologies Corporation Oil scavenge system for a gas turbine engine
US9074609B2 (en) * 2011-02-15 2015-07-07 Siemens Energy, Inc. Gas turbine engine
FR2984777B1 (fr) * 2011-12-23 2014-09-05 Snecma Procede de fabrication d'un arbre de turbomachine

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Publication number Priority date Publication date Assignee Title
US4086759A (en) * 1976-10-01 1978-05-02 Caterpillar Tractor Co. Gas turbine shaft and bearing assembly
JP2816583B2 (ja) * 1989-11-22 1998-10-27 ヤンマーディーゼル株式会社 ２軸式非常用ガスタービン
US20030059295A1 (en) * 2001-09-26 2003-03-27 Olsen Andrew J. Interchangeable power turbine cartridge assembly
US20100111691A1 (en) * 2008-11-06 2010-05-06 Honeywell International Inc. Turbine engine components
US20110305572A1 (en) * 2009-03-24 2011-12-15 Rolls-Royce Plc Mechanical arrangement

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Title
See also references of EP2989299A4 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201800006394A1 (it) * 2018-06-18 2019-12-18 Sistema di spurgo per cassa cuscino
WO2019242888A1 (fr) * 2018-06-18 2019-12-26 Nuovo Pignone Tecnologie - S.R.L. Dispositif de dégazage de carter de palier
KR20210016428A (ko) * 2018-06-18 2021-02-15 누보 피그노네 테크놀로지 에스알엘 베어링 섬프용 통기 시스템
US11352952B2 (en) 2018-06-18 2022-06-07 Nuovo Pignone Tecnologie Srl Venting system for bearing sump
KR102529655B1 (ko) 2018-06-18 2023-05-04 누보 피그노네 테크놀로지 에스알엘 베어링 섬프용 통기 시스템

Also Published As

Publication number Publication date
EP2989299A4 (fr) 2017-01-18
EP2989299A1 (fr) 2016-03-02
US20160069211A1 (en) 2016-03-10

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