US3366365A - Turbines - Google Patents

Turbines Download PDF

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Publication number
US3366365A
US3366365A US487696A US48769665A US3366365A US 3366365 A US3366365 A US 3366365A US 487696 A US487696 A US 487696A US 48769665 A US48769665 A US 48769665A US 3366365 A US3366365 A US 3366365A
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US
United States
Prior art keywords
casing
turbine
main
rotor
bearing
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.)
Expired - Lifetime
Application number
US487696A
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English (en)
Inventor
Rizk Waheeb
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.)
English Electric Co Ltd
Original Assignee
English Electric Co Ltd
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 English Electric Co Ltd filed Critical English Electric Co Ltd
Application granted granted Critical
Publication of US3366365A publication Critical patent/US3366365A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep

Definitions

  • a turbine has its rotor mounted in bearing-supporting structure, which is mounted on a foundation, and has its main pressure-containing casing, through which gas is supplied to the rotor, supported and positioned independently of the bearing-supporting structure, in a way to allow thermal expansion of the main pressure-containing casing while maintaining it accurately concentric with the rotor, by means including:
  • This invention relates to turbines.
  • a gas power turbine includes an overhung turbine rotor mounted in bearings in bearing-supporting structure which is mounted on a foundation, the turbine rotor carrying rotor blades, stator blades cooperating with said rotor blades, and means including a main pressure-containing casing within which gas ows to said stator blades to drive the rotor, said main pressure-containing casing being mounted, independently of said bearing-supporting structure, on a foundation by means preventing translation of rotational movement of said main casing relative to the foundation, in each of the six degrees of freedom, but allowing thermal expansion radially and longitudinally of the axis of rotation from a point on said axis.
  • FIG. 1 is a section on the vertical centre-line of a gase power turbine
  • FIG. 2 is a plan View of the turbine of FIG. 1,
  • FIG. 3 is a section on the line III-III of FIG. 2,
  • FIG. 4 is a section on the line IV-IV of FIG. 2,
  • FIG. 5 is a detail view
  • FIG. 6 is a view on the line VI-VI of FIG. 5.
  • the turbine comprises bearing-supporting structure 10, in which the turbine shaft 11 is supported by means of two plain bearings 12, and a thrust bearing 13, spaced along the shaft.
  • the overhung turbine rotor 14 is bolted to the shaft 11 which drives an alternator (not shown) through a flanged connection.
  • the structure is mounted on a xed base plate 15, which is secured to a foundation.
  • the turbine has rotor blades 16, and stator blades 17. The latter are supported in a circular assembly in a main casing 20, which forms the principal pressure-containing casing of the turbine.
  • Gas is led to the main casing 20 from a gas source, eg., two simple open-cycle gas turbine engines, through ducts 21 which are bolted to flanges formed on the main casing and on an end closure casing 22.
  • the gas stream is conveyed within inner liners 23 in the ducts 21, cooperating with a corresponding liner 24 within the main casing 20, the latter liner 24 having an annular outlet cooperating with the stator blades 17
  • the main casing 20 of the turbine is not xed relative to the structure 10, but is mounted in the following way, on the base plate 15.
  • a pair of axially-spaced flanges 27, 28 are formed on the main casing 20 adjacent the plane of rotation of the rotor and are pin-jointed to a pair of supporting plates 29, 30 by means of pins 31, 32, passing through a bore in an enlarged end of each plate, substantially at opposite sides of the horizontal diameter of the turbine rotor 14.
  • the lower ends of the supporting plates 29, 30 are secured by setscrews to blocks 33, 34, which are in turn secured to the xed base plate 15.
  • the blocks 33, 34 are each provided with inclined keys 35, 36 which engage in keyways 37, 38 formed between the anges 27, 28 on the main casing 20, one on each side of the casing.
  • the blocks 33, 34 are nally secured to, and located with respect to, the base plate 15 when the main casing 29 has been positioned so that the correct clearances are obtained between the stationary and rotating parts of the turbine.
  • a key 43 which engages with a keyway member 44 secured to the base plate 15 and with an axial keyway cut in the anges 27, 28 at the lower end of the vertical diameter of the main casing 20.
  • Two tension rods 45 connect the outer casings of the ducts 21 to a pair of torsion bars 46 which are anchored through blocks 47 to base plates 48, which are secured to the same foundation as base plate 15.
  • the free ends of torsion bars 46 are supported in blocks 49 and have levers 50 secured to them by keys.
  • the two ends of each tension rod 45 are secured respectively to a lever 50 and to a duct 21 through pin-and-ball joints allowing limited universal movement.
  • the torsion bars 46 are pre-loaded on assembly so that the levers 50 are vertical when the tension force in rods 45 reaches a predetermined ligure expected in operation.
  • a further pair of rods 51 is provided, which are connected through spherical joints at their upper ends to the end closure casing 22 substantially on the horizontal centre-line of the turbine, and through spherical joints at their lower ends to the base plate 15.
  • the rods 51 are nearly vertical.
  • a ring member 52 having grooves containing sealing rings 53 is secured to a flange of the structure 10.
  • the sealing rings 53 engage a vertical face on the end closure casing 22, which is secured by bolting flanges to the main casing 20.
  • the ring member 52 also has an annular projection 54 which extends into a rebate 55 in the end closure casing 22, the clearance being chosen to permit thermal expansion of the structure 10 (e.g., due to rotation of the alternator with the turbine cold) relative to the casings 20, 22, in addition to permitting thermal expansion of the latter relative to the structure 10, which occurs when the turbine is supplied with high-temperature gas.
  • the main casing 20 of the turbine is allowed to move relative to the structure 10 in which the turbine rotor 14 is located, the ring member 52 being capable of moving independently of the end closure casing 22 while the sealing rings 53 remain in sealing contact.
  • the turbine rotor 14 is mounted through the structure 10, directly on the base plate 15.
  • the main casing 20, on the other hand, is mounted independently; its weight is supported by rst means including plates 29, 30, which also locate the main casing against vertical translational movement and against torsional loads (i.e., against turning about the rotational axis of the turbine). A small proportion of its weight may also be supported by rods 51.
  • the axial position of the main casing 2G is determined by second means including the keys 35, 36, which oppose end loads on the main casing and locate it against axial translational movement, and against turning about a vertical axis.
  • the main casing 20 is centralised, i.e., located in the horizontal plane relative to the base plate 15, by third means including the key 43 which withstands lateral forces and locates the main casing against transverse translational movement.
  • the main casing 20 is located against rocking about a transverse horizontal axis by fourth means including the rods 51.
  • a turbine including an overhung turbine rotor comprising a turbine disc, a plurality of rotor blades secured to said turbine disc, and a shaft, said turbine disc being secured to an end of said shaft; a bearing-supporting structure; a foundation; said bearing-supporting structure being mounted on said foundation; means rotatably to mount said overhung turbine rotor in said bearingsupporting structure; a main pressure-containing casing mounted on said foundation; stator blades mounted within said main pressure-containing casing and cooperating with said rotor blades; and gas supply means which supplies gas through said main pressure-containing casing and said stator blades to said rotor blades to drive said rotor; load bearing and locating means positioning and supporting said main pressure-containing casing on said foundation independently of said bearing-supporting structure, said load bearing and locating means including:
  • said gas sealing means comprising a ring member secured to the radial flange formed on said bearing-supporting structure, a pluralityrof annular grooves formed in said ring member and a plurality of sealing rings each retained in a respective annular groove and engaging said radial end-face formed on said main pressurecontaining casing; said gas sealing means being capable of allowing relative expansion of said bearing-supporting structure and said main pressure-containing casing in a direction at right angles to the axis of rotation of said overhung turbine rotor.
  • thrust relieving means including (i) a pre-loaded torsion bar having two ends;
  • said thrust relieving means is capable of relieving an axial thrust imposed on saidmain pressurecontaining casing by gas forces acting thereon.
  • said gas sealing means being capable of allowing relative expansion of said bearing-supporting structure and said main pressure-containing casing in a direction at right angles to the axis of rotation of said overhung turbine rotor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pinball Game Machines (AREA)
  • Control Of Turbines (AREA)
  • Pivots And Pivotal Connections (AREA)
US487696A 1964-09-29 1965-09-16 Turbines Expired - Lifetime US3366365A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB39703/64A GB1080747A (en) 1964-09-29 1964-09-29 Improvements in or relating to turbines

Publications (1)

Publication Number Publication Date
US3366365A true US3366365A (en) 1968-01-30

Family

ID=10411014

Family Applications (1)

Application Number Title Priority Date Filing Date
US487696A Expired - Lifetime US3366365A (en) 1964-09-29 1965-09-16 Turbines

Country Status (6)

Country Link
US (1) US3366365A (de)
CH (1) CH516736A (de)
DE (1) DE1476763B1 (de)
ES (1) ES317885A1 (de)
GB (1) GB1080747A (de)
SE (1) SE329935B (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3460806A (en) * 1967-09-08 1969-08-12 Garrett Corp Floating nozzle and shroud construction for gas turbine
US3837164A (en) * 1972-05-24 1974-09-24 Rolls Royce 1971 Ltd Industrial gas turbine power plant mounting apparatus
US3860359A (en) * 1973-07-30 1975-01-14 Curtiss Wright Corp Mounting system for gas turbine power unit
US6196795B1 (en) * 1996-02-13 2001-03-06 Kvaerner Energy A.S. Turbine pack and method for adapting a turbine pack
US7175385B2 (en) 2003-12-15 2007-02-13 Man Turbo Ag Mounting of the rotor of a gas turbine
US20170292408A1 (en) * 2016-04-08 2017-10-12 Ansaldo Energia Switzerland AG Assembly, in particular of engine components

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4053189A (en) * 1976-06-17 1977-10-11 United Technologies Corporation Turbine construction
IT1138763B (it) * 1981-05-04 1986-09-17 Nuovo Pignone Spa Perfezionamenti in una turbina a gas di potenza
US5051061A (en) * 1988-12-23 1991-09-24 Asea Brown Boveri Ltd. Multi-cylinder steam turbine set
EA007359B1 (ru) * 2004-07-12 2006-10-27 Всеволод Константинович Балабанович Способ работы турбомашины балабановича малой мощности и устройство для его реализации (турбомашина балабановича малой мощности)
ITMI20042486A1 (it) * 2004-12-23 2005-03-23 Nuovo Pignone Spa Turbogeneratore

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2789787A (en) * 1949-10-22 1957-04-23 Svenska Turbinfab Ab Guide blade device for steam or gas turbines
US2828939A (en) * 1950-09-20 1958-04-01 Power Jets Res & Dev Ltd Support of turbine casings and other structure
US3036375A (en) * 1959-05-14 1962-05-29 Gen Electric Method of mounting machines
US3072380A (en) * 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1682317A (en) * 1928-08-28 Turbine support
DE626540C (de) * 1933-07-01 1936-02-27 Carl Schmieske Einteiliger ringfoermiger Duesenkasten fuer Dampf- oder Gasturbinen
DE832815C (de) * 1944-07-19 1952-02-28 Maschf Augsburg Nuernberg Ag Anordnung der Teilturbinen einer Gasturbinenanlage
DE873016C (de) * 1944-07-25 1953-04-09 Siemens Ag Zusammenbau einer Gasturbine mit der Brennkammer
DE904366C (de) * 1944-08-19 1954-02-18 Siemens Ag Anordnung an der Brennkammer einer nach dem Gleichdruckverfahren arbeitenden Gasturbinenanlage
GB609596A (en) * 1946-03-18 1948-10-04 Parsons C A & Co Ltd Improvements in or relating to gas turbine plant
NL71636C (de) * 1946-05-07
US2443054A (en) * 1946-11-07 1948-06-08 Westinghouse Electric Corp Gas turbine plant
US2650753A (en) * 1947-06-11 1953-09-01 Gen Electric Turbomachine stator casing
GB624298A (en) * 1947-06-30 1949-06-01 Arthur Holmes Fletcher Improvements relating to gas turbine power plants
CH294844A (de) * 1950-09-20 1953-11-30 Power Jets Res & Dev Ltd Einrichtung zum Abstützen von grossen Temperaturunterschieden ausgesetzten Kraftmaschinengehäusen, insbesondere Austrittsgehäusen von Gasturbinen.
GB743633A (en) * 1952-12-31 1956-01-18 Gen Motors Corp Improvements in or relating to gas turbine engines
GB726072A (en) * 1953-01-29 1955-03-16 Parsons & Marine Eng Turbine Improvements in and relating to elastic fluid turbines
GB722740A (en) * 1953-04-01 1955-01-26 Rolls Royce Improvements relating to gas turbine engines
DE972115C (de) * 1954-10-23 1959-05-21 Maschf Augsburg Nuernberg Ag Axialdurchstroemte Turbine fuer heisse Treibmittel, insbesondere Gasturbine
DE1013466B (de) * 1955-03-29 1957-08-08 Tech Studien Ag Abstuetzung einer Maschinen-Apparategruppe einer Waermekraftanlage

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2789787A (en) * 1949-10-22 1957-04-23 Svenska Turbinfab Ab Guide blade device for steam or gas turbines
US2828939A (en) * 1950-09-20 1958-04-01 Power Jets Res & Dev Ltd Support of turbine casings and other structure
US3072380A (en) * 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting
US3036375A (en) * 1959-05-14 1962-05-29 Gen Electric Method of mounting machines

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3460806A (en) * 1967-09-08 1969-08-12 Garrett Corp Floating nozzle and shroud construction for gas turbine
US3837164A (en) * 1972-05-24 1974-09-24 Rolls Royce 1971 Ltd Industrial gas turbine power plant mounting apparatus
US3860359A (en) * 1973-07-30 1975-01-14 Curtiss Wright Corp Mounting system for gas turbine power unit
US6196795B1 (en) * 1996-02-13 2001-03-06 Kvaerner Energy A.S. Turbine pack and method for adapting a turbine pack
US7175385B2 (en) 2003-12-15 2007-02-13 Man Turbo Ag Mounting of the rotor of a gas turbine
US20170292408A1 (en) * 2016-04-08 2017-10-12 Ansaldo Energia Switzerland AG Assembly, in particular of engine components
CN107269330A (zh) * 2016-04-08 2017-10-20 安萨尔多能源瑞士股份公司 组件，尤其发动机部件的组件
US10746055B2 (en) * 2016-04-08 2020-08-18 Ansaldo Energia Switzerland AG Floating support assembly for compensating for axial thermal expansion

Also Published As

Publication number Publication date
GB1080747A (en) 1967-08-23
SE329935B (de) 1970-10-26
DE1476763B1 (de) 1970-04-23
CH516736A (fr) 1971-12-15
ES317885A1 (es) 1966-03-16

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