US3304054A - Housing for a gas or steam turbine - Google Patents

Housing for a gas or steam turbine Download PDF

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Publication number
US3304054A
US3304054A US516538A US51653865A US3304054A US 3304054 A US3304054 A US 3304054A US 516538 A US516538 A US 516538A US 51653865 A US51653865 A US 51653865A US 3304054 A US3304054 A US 3304054A
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United States
Prior art keywords
ring
inner housing
intermediate space
guide
housing
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
US516538A
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English (en)
Inventor
Oechslin Konrad
Moser Paul
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Sulzer Escher Wyss AG
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Escher Wyss AG
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Publication date
Application filed by Escher Wyss AG filed Critical Escher Wyss AG
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    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • This invention relates to a housing for a -gas or steam turbine, having an outer housing and an inner housing, fthe latter comprising a stationary guide apparatus, a partition separatin-g the intermediate space between inner and outer housing into an inlet-side intermediate space and an outlet-side intermedaite space, and a supporting eletment for the inner housing.
  • Housings of this kind are used more particularly when the working medium under pressure has high temperatures.
  • the inner housing then serves for guiding the flow of working medium and as Sup-port for the guide 'blades of the turbine, and the intermediate space between the housings contains a heat insulating material, the inner housing taking up substantially the inner temperature, and the outer housing the inner pressure.
  • connection between the outer housing and that part part of the inner housing which receives the guide blades must take up the temperature ⁇ gradient occurring between the housings, as well as the forces acting axially on the ⁇ guide blades in the direction of the outlet-side, and at the same time, keep the lguide -blades as far as possible in the same position in relation to the moving blades.
  • Flange holding means are known, lin which the flange is provided on the outlet-side end of the inner housing portion receiving the guide blades, and at the same time forms the partition between the inlet-side intermediate space and the outlet-side intermediate space between the housings.
  • This embodiment apart from the advantage of the axially compact construction, has considerable disadvantages.
  • the rotor shaft is ⁇ advantageously mounted on the inlet-side axially outside the turbine housing, and if necessary is cooled from that side up to the first guideblade ring exclusive.
  • the rotor In operation, the rotor is heated substantially from the first moving-'blade ring onward, and expands axially from that place in the direction towards the outlet-side of the turbine.
  • the inner housing portion, receiving .the guide blades and heated in like manner in operation is, on the contrary, xed by its outlet-side end to the holding ange, and is fixed by means of the latter relatively to the outer housing, and the inner housing portion receiving .the guide blades therefore expands axially -towards the inlet-side.
  • a turbine housing of the kin-d hereinbefore described is developed, according to the invention, in that the inlet-side narrower end of the truste-conical shell carries the inletside end of a substantially cylindrical supporting ring, which surrounds the inner housing at least over part of the portion of the latter receiving the guide blades, and the outlet-side end of which carries the inner housing, the frusto-conical shell in the manner known per se, and/or the supporting ring having openings in the part thereof situated in the linlet-side intermediate space.
  • FIG. l shows an axial section through a housing of a gas turbine
  • FIG. 2 shows a portion of a section at right angles to the axis on the line II--ll in FIG. 1.
  • the turbine housing has an outer housing 1 and an inner housing, which on the inlet side comprises the inlet part 2 and the port-ion 4 receiving the guide blades 3.
  • 5 denotes t-he rotor carrying the discs 6 with the moving blades 7.
  • Both the inlet-side part 8 and the outlet-side part 9 of the intermediate space between the housings is filled with heat insulating material 10.
  • the sealing ring 17 in known manner, consists of an outer ring 18, mounted axially fast in a sealing manner in the outer housing 1, and an inner ring 19, co-axial with said ring 18 and secured to the outlet-side end of ring 16, the co-axial play provided between rings 18, 19 being bridge-d by a thin, one-part diaphragm 20.
  • a two part frusto-conical shell 21 is secured as supporting element by its wider orifice to the ring 12.
  • This frusto-conical shell 21 has a thin wall thickness and consists of austenitic material of low thermal conductivity.
  • the rotor 5 is mounted axially outside the turbine, not shown in the drawing, in an air compressor, assembled with it.
  • a gap 22, recessed between the rotor shaft and a tubular part of the outer housing 1 allows cool working medium from the air compressor to flow along the rotor shaft to the first guide-blade ring.
  • the inlet part 2 of the inner housing is centred radially and axially movable in the cold compressor housing 24 by means of four cotters 23, and the inner housing portion 4 receiving the guide blades 3 is centred radially and axially movable in the region of its inlet-side end by means of four cotters 25.
  • the outlet-side end of the supporting ring 27 is connected to the ring 16, which is situated on the outlet-side of the last guide blade ring and surrounds the last moving blade ring.
  • the supporting ring 27 together with the ring 16 surrounds the three outermost guide and movingblade rings situated downstream.
  • the supporting ring 27 has longitudinal slots 29, the Wall parts between the longitudinal slots in the peripheral direction being a multiple of the wall thickness, and the space bounded by the frusto-conical shell 21, the supporting ring 27 and the sealing ring 17 being also lilled with heat insulating material 10.
  • the rotor with the discs 6 and the moving blades 7 ixed to the latter is heated by the hot working medium and expands axially in the direction towards the outlet-side of the turbine.
  • the inner-housing portion 4 receiving the guide blades 3 is also heated mostly by the working medium flowing through the guide blades and moving blades, and to a lesser extent by the heat passing through the inlet par-t 2 of the inner housing through the insulating material 10.
  • the supporting ring 27 is heated mostly by the ring 16, and to a lesser extent by the heat passing from the inner housing through the' insulating material 10, so that it has approximately the same temperature as the inner-housing portion 4 receiving the guide blades.
  • the maximum temperature namely that of the supporting ring 27, is imparted to the frustoconical shell 21 at its line of contact with the iiange 26, while its lowest temperature, substantially corresponding to the temperature of the outer housing 1, lies on its line of contact with the ring 12.
  • the effect of this is that the axial expansion of the frusto-conical shell 21 remains within insignificant limits, like that of the known embodiment, and that the region of the ange 26 is displaced by an insigniticant amount only, in the direction towards the inlet-side of the turbine.
  • this portion 4 as Well as the supporting ring 27 are heated essentially approximately equally, and :all these parts consist of material having the same thermal expansion, the guide blades 3 and moving blades 7 of the turbine remain inapproximately the same axial position relatively to each other Within theV entire working range.
  • Thevthermal expansion of the frusto-conical shell 21 may be reduced additionally in manner known per se by means of holes therein, and the thermal expansion of the supporting ring 27 may be increased by omitting insulating material between supporting ring and inner housing, and in this Way, minimum relative displacement between guide-blade apparatus and moving-blade apparatus is effected.
  • the axial thrust acting on the guide blades 3, or on the inner-housing portion 4 receiving said blades, during the operation of the turbine, in the direction towards the outlet-side is transmitted by the ring 16 to the supporting ring 27, by the latter to the frusto-conical shell 21 and by the latter to the outer housing 1. Due to the step according to the invention of the use of a supporting ring, the innerhousing portionl receiving the guide blades is subjected exclusively to compression stresses.
  • the guide blades 3 are mounted in tive two-part guideblade rings 30, the corresponding halves being connected together by screws 31. Between each pair of adjacent guide-blade rings, there is arranged one of a total of four one-part intermediate rings 32. Each of these four intermediate rings 32 surrounds a moving-blade ring 6, 7, and the outlet-side last moving-blade ring of the total of five such rings is surrounded by the ring 16, which has an inner radial groove 33, in which 4an outer radial key 34 of the outlet-side last guide-blade ring is held fast axially.
  • the said outlet-side last guide-,blade ring is centred 4 radially movable in the ring 16 by means of four cotters 35', which cotters also transmit the torque of the innerhousing portion 4, carrying the guide blades, to the ring 16.
  • the intermediate rings y32 have on each end face an inner rim 35,which engages with close t a corresponding recess 36 of the respectively contiguous guide-blade ring 30, whereby each guide-blade ring is centred relatively to the intermediate ring immediately adjacent it.
  • Each guide-blade ring 304 has an outer peripheral groove 37.
  • Each intermediate ring 32 is connected to the two adjacent guide-blade rings 30 by means of screwbolts 38 passing throughthe intermediate -ring 32 and extending into the peripheral grooves 37 of the guide-blade rings 30, the nuts of the screwbolts 38 lying in the peripheral grooves 37 of the guide-blade rings 30,
  • the rings 30, 32, 30, connected together in each case by a ring of such screwbolts, are connected together non-rotatably, by a ring of axial cotters 39, which extend over all three rings and are accommodated in axially flush grooves 40.
  • Non-circularity of the individual guide-blade rings'30 on heating, due to their two-part construction, and owing to the irregularity of the cross section of the material in the peripheral direction at the joints of the two halves, necessarily associated with such construction, is kept within-negligibly small limits by the one-part intermediate rings 32, or the mutual centring of the guide-blade rings relatively to the intermediate rings.
  • the individual rings 30, 32 are pressed against the rings which, seen from the position of the ring in question, are on the outlet-side of them, and the latter are pressed against the ring 16 supported axially in the outer housing 1 through the supporting rin-g 27 and the frusto-conical shell 21, the screwbolts 38 having no important tensile forces to take up.
  • the high stability of the inner-housing portion receiving the guide blades makes it possible to construct this portion of light weight and with comparatively thin walls, whereby a considerable saving in heat-resistant material is eiected.
  • an outer housing and an inner housing said housings confining an intermediate space; heat insulating material disposed in said intermediate space; a plurality of axially spaced circular series of inwardly extending guide blades arranged over an axial portion of said inner housing; said axial portion of said inner housing and said guide blades thus forming a stationary-guide apparatus; a partition separating said intermediate space into an inlet-side intermediate space and an outlet-side intermediate space; means for connecting axially fast in a sealing manner and for centering said partition non-rotatably relatively to said outer housing; means for centering and for connecting in a sealing manner said inner housing to said partition to be axially displaceable relatively to the latter; a supporting element for supporting said inner housing, having a thin-walled frusto-conical shell consisting of material of low thermal conductivity, arranged in 4said inlet-side intermediate space, co-axial with said inner housing, -its wider end facing said partition, and means for connecting axially fast and
  • said partition comprises a ring; inwardly extending lugs fixed at said ring having at their inner ends cotters for centering said inner housing; a sealing ring for bridging the openings left free by said lugs, said sealing ring comprising an outer ring mounted axially fast in a sealing manner on said ring and an inner ring co-axial with said outer ring and mounted axially fast in a sealing manner on said inner housing, and a thin corrugated one-part diaphragm bridging the co-axial play between said rings of said sealing ring.
  • said means for connecting axially fast and for centering nonrotatably said wider end of said -frusto-conical shell relatively to said outer housing comprises a ring rigidly connected with said wider end of said frusta-conical shell, a inner peripheral groove in said outer housing, said ring engaging with close axial fit in said groove, and cotters.
  • said means for connecting axially fast and for centering nonrotatably said outlet-side end ⁇ of said supporting ring relatively to said inner housing comprise a radial groove in one of said two parts and a corresponding radial key in the other of said two parts, said key engaging with close axial fit in said groove, and cotters.
  • said guide apparatus comprises a plurality of axially spaced diametrically split two-part guide-blade rings each receiving one of said circular series of guide blades, a plurality of one-part intermediate rings, arranged so as to alternate contiguously with said guide-blade rings, and means for centering and for non-rotatably connecting said rings relatively to each other.
  • a diametrically split two-part outer housing and an inner housing said housings confining an intermediate space; heat insulating material disposed in said intermediate space, said inner housing comprising a diametrically split two-part inletportion, a guide apparatus portion and a diametrically split two-part outlet-portion; said guide apparatus portion comprising a plurality of axially spaced .diametrically split two-part guide-blade rings each having a circular series of inwardly extending guide blades; a plurality of one-part intermediate rings, arranged so as to alternate contiguously with said guide-blade rings; said rings thus forming a stationary guide apparatus; said intermediate rings having on their end faces an inner rim, and said guide-blade rings having on their end faces facing one of said intermediate rings a corresponding recess, each of said rims engaging with close fit in the corresponding recess so as to center said guide-blade rings and said intermediate rings relatively to each other; each of
  • connection ring thus forming said outlet- References Cited by he'EXaIIlillel' side end of said guide apparatus, said outlet-side last of 5 UNITED STATES PATENTS said guide blade rings having an outer radial key, and said 2,445,661 ,H1948 Constant et al.
  • connection ring having an inner radial groove, said key engaging with close axial t in said groove, so as to con- MARTIN P SCHWADRON prima] Examiner nect axially fast said outlet-side end of said supporting v y ring to said outlet-side end of said guide apparatus, and 10 E. A. POWELL, JR., Assistant Examiner-

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
US516538A 1965-01-12 1965-12-27 Housing for a gas or steam turbine Expired - Lifetime US3304054A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH37265A CH421142A (de) 1965-01-12 1965-01-12 Gehäuse für eine Gas- oder Dampfturbine

Publications (1)

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US3304054A true US3304054A (en) 1967-02-14

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US516538A Expired - Lifetime US3304054A (en) 1965-01-12 1965-12-27 Housing for a gas or steam turbine

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US (1) US3304054A (forum.php)
BE (1) BE674025A (forum.php)
CH (1) CH421142A (forum.php)
DE (1) DE1426801A1 (forum.php)
FR (1) FR1459676A (forum.php)
GB (1) GB1137512A (forum.php)
NL (1) NL6517281A (forum.php)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652178A (en) * 1968-11-28 1972-03-28 Bennes Marrel Device for the output shaft of a gas turbine
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4525998A (en) * 1982-08-02 1985-07-02 United Technologies Corporation Clearance control for gas turbine engine
US4534700A (en) * 1983-01-18 1985-08-13 Bbc Brown, Boveri & Company, Limited Externally mounted exhaust-gas turbocharger with uncooled gas duct
US4578942A (en) * 1983-05-02 1986-04-01 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Gas turbine engine having a minimal blade tip clearance
US4875828A (en) * 1985-03-14 1989-10-24 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Turbo-engine having means for controlling the radial gap
US5630702A (en) * 1994-11-26 1997-05-20 Asea Brown Boveri Ag Arrangement for influencing the radial clearance of the blading in axial-flow compressors including hollow spaces filled with insulating material
CN102216568A (zh) * 2008-11-05 2011-10-12 西门子公司 用于燃气轮机的轴向段的导向叶片支架
US20170067362A1 (en) * 2015-09-08 2017-03-09 Ansaldo Energia Switzerland AG Gas turbine rotor cover

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0118051B1 (de) * 1983-03-04 1988-02-03 BBC Brown Boveri AG Verbindung zwischen warmen und kalten Teilen bei ungekühlten Abgasturboladern
DE3509193A1 (de) * 1985-03-14 1986-09-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Stroemungsmaschine mit innengehaeuse
RU2124640C1 (ru) * 1997-06-27 1999-01-10 Закрытое акционерное общество "ОРМА" Способ монтажа внутренних вставок корпуса турбины газоперекачивающего агрегата
US10677260B2 (en) * 2017-02-21 2020-06-09 General Electric Company Turbine engine and method of manufacturing
CN114542210B (zh) * 2022-03-09 2023-12-05 中国船舶重工集团公司第七0三研究所 一种汽轮机隔板持环的定位结构

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445661A (en) * 1941-09-22 1948-07-20 Vickers Electrical Co Ltd Axial flow turbine, compressor and the like

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2445661A (en) * 1941-09-22 1948-07-20 Vickers Electrical Co Ltd Axial flow turbine, compressor and the like

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652178A (en) * 1968-11-28 1972-03-28 Bennes Marrel Device for the output shaft of a gas turbine
US4101242A (en) * 1975-06-20 1978-07-18 Rolls-Royce Limited Matching thermal expansion of components of turbo-machines
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4525998A (en) * 1982-08-02 1985-07-02 United Technologies Corporation Clearance control for gas turbine engine
US4534700A (en) * 1983-01-18 1985-08-13 Bbc Brown, Boveri & Company, Limited Externally mounted exhaust-gas turbocharger with uncooled gas duct
US4578942A (en) * 1983-05-02 1986-04-01 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Gas turbine engine having a minimal blade tip clearance
US4875828A (en) * 1985-03-14 1989-10-24 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Turbo-engine having means for controlling the radial gap
US5630702A (en) * 1994-11-26 1997-05-20 Asea Brown Boveri Ag Arrangement for influencing the radial clearance of the blading in axial-flow compressors including hollow spaces filled with insulating material
CN102216568A (zh) * 2008-11-05 2011-10-12 西门子公司 用于燃气轮机的轴向段的导向叶片支架
US8870526B2 (en) 2008-11-05 2014-10-28 Siemens Aktiengesellschaft Axially segmented guide vane mount for a gas turbine
CN102216568B (zh) * 2008-11-05 2015-11-25 西门子公司 用于燃气轮机的轴向段的导向叶片支架
US20170067362A1 (en) * 2015-09-08 2017-03-09 Ansaldo Energia Switzerland AG Gas turbine rotor cover
US10443433B2 (en) * 2015-09-08 2019-10-15 Ansaldo Energia Switzerland AG Gas turbine rotor cover

Also Published As

Publication number Publication date
CH421142A (de) 1966-09-30
NL6517281A (forum.php) 1966-07-13
FR1459676A (fr) 1966-11-18
GB1137512A (en) 1968-12-27
BE674025A (forum.php) 1966-04-15
DE1426801A1 (de) 1969-07-17

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