US3740164A - Deflection control means for machine housings - Google Patents

Deflection control means for machine housings Download PDF

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Publication number
US3740164A
US3740164A US00227431A US3740164DA US3740164A US 3740164 A US3740164 A US 3740164A US 00227431 A US00227431 A US 00227431A US 3740164D A US3740164D A US 3740164DA US 3740164 A US3740164 A US 3740164A
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US
United States
Prior art keywords
housing
ring
sections
rings
rotor
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
US00227431A
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English (en)
Inventor
F Zerlauth
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.)
Brown Boveri Sulzer Turbomaschinen AG
Sulzer Escher Wyss AG
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
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
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Assigned to SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND reassignment SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR
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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the mating parts of thering are rotatable about a common axis and are of varying thickness so that relative rotation of the mating parts causes an increase or decrease in the amount of sag or deflection of the housing at that point.
  • the difference in deadweight sag between the rotor and the housing can thus be held to a minimum.
  • This invention relates to a deflection control means for machine housings, and particularly, for machine housings subject to elastic deformation under deadweight.
  • the invention provides a ring made of two part-rings which bear on one another and which are inserted at a junction between two housing portions.
  • the plane of division between the two part-rings is inclined in relation to the contact planes directed towards the housing sections or portions so that the contact planes can be adjusted relative to one another to a selective angle by turning the part-rings in relation to one another.
  • the differences between the housing axis flexure clue to deadweight and the rotor axis flexure due to deadweight can be kept at a minimum. In this way, it is possible to maintain a minimum clearance between the rotor and housing.
  • the rings can also be used to correct any machining errors at the places where the housing sections come together, for example, at the flanges.
  • Each of the part-rings can be divided two or more times about the periphery so as to form arcuate segments.
  • the ring parts can be secured in place and retained in any suitable fashion such as by releaseable straps.
  • FIG. 1 illustrates a longitudinal sectional view of a part of a machine housing utilizing a ring according to the invention
  • FIG. 2 illustrates a detail of the ring of FIG. I to an enlarged scale
  • FIG. 3 illustrates a partial longitudinal sectional view of a gas-turbine unit incorporating a ring therein according to the invention.
  • FIG. 4 illustrates a view of an exhaust gas turbine supercharger unit for internal combustion engines utilizing a ring according to the invention.
  • two housingparts l and 2 of a machine are interconnected by means of flanges 3 and 4 each of which is perpendicular to the machine axis 5.
  • An intermediate ring 6 is inserted between these flanges 3, 4 and consists of two part-rings 7 and 8.
  • the plane of contact between these part-rings 7 and 8 is inclined in relation to the planes of contact of the ring 6 with the flanges 3 and 4 of the machine housing parts 1, 2.
  • the flanges 3, 4 and the part-rings 7, 8 have bores 9 (FIG. 2) which are spaced at a uniform pitch t over the periphery of a pitch circle 10.
  • the inclination of the flanges 3, 4 of the housing parts 1, 2 in relation to one another are adjusted by turning the part-rings 7, 8 on the pitch circle 10 so that the flexure of the housing axis 5 due to the deadweight can be changed, either by increasing or by decreasing the degree of flexure.
  • the difference between the flexure of the housing axis 5 due to deadweight and the flexure of the axis of a rotor (not shown) surrounded by the housing can be adjusted to approach a minimum value.
  • This adjustment can'be carried out on assembly and needs no further modification as operation progresses, since experience has shown that there are practically no further changes in the housing, for example, due to material creep.
  • the housing can be supported and the bolts removed and then the rings 7, 8 can be displaced in relation to one another so that in the: renewed state of the material the minimum dimension of the difference in flexure between the housing and the rotor 6 is restored to a minimum value.
  • the connection of the straps ll, 12 to the part-ring halves is made, for example, by means of screw bolts 13 with countersunk heads.
  • a gas turbine plant comprises a gas turbine 20 and a compressor 21. Air for combustion is drawn from a feed duct 22 by the compressor 21 and delivered in the compressed state through a duct 23 to combustion chambers (not shown) disposed around the gas turbine 20. The combustion gas flows through a duct 24 into the gas turbine blading and then through a duct 25 to an exhaust gas housing 26 of the machine as is known.
  • a compressor rotor 27 and a turbine rotor 28 are constructed as an integral member which is supported in bearings 29 and 30.
  • the turbine housing is made up ofindividual sections 31, 32 and 33.
  • the compressor housing may also be made up of a number of sections, one of which, 34, can be seen at the compressor and adjacent the turbine.
  • the housing sections 31 to 34 provide a tubular housing which is supported on a base plate 37 by suitable support members 35 and 36. These support members 35, 36 are disposed substantially in the central planes 38 and 39 of the bearings 29 and 30. Between these bearings 29, 30, both the housing 31 34 and rotor 2728 experience flexure corresponding to gravity, the axes of flexure having considerable differences in practice in every case.
  • the housing flexure is adapted to the rotor flexure by turning the halves of this ring 6 suitably in relation to one another, so that the different flexures are brought to a minimum at every part of the machine length. In most cases, it will be necessary to increase the housing flexure by means of this ring 6 because the natural flexure of the housing 3l34 is less than that of the rotor 27-28.
  • an exhaust gas turbine supercharger unit has a rotor 40 disposed inside a housing made up of sections 41, 42, 43 and 44. In the middle region, this housing is supported by the claws 45 of a bracket 46 of an internal combustion engine (not shown). In addition, the housing section 41 supports a bearing 47 and the housing section 44 supports a bearing 48.
  • the housing 41-44 is thus bent downwards at the ends by the deadweight and, more particularly, by the bearing loading, so that the housing axis appears to be bent upwards while the rotor 40 mounted at the two ends thereof is bent downwards. Consequently, the seals in the middle of the rotor 40 and at the turbine and compressor rotors are subject to considerable displacements in relation to the housing surrounding these parts.
  • a ring 6 as described above and as shown in FIGS. 1 and 2 is incorporated at least between the flanges of the housing sections 42 and 43.
  • the gap between the compressor rotor 49 and the stationary cover disc 50 can thus be ad justed to a minimum value by adjustment of the optimum wedge angle for the ring 6 so that efficiency can be increased accordingly by reduction of the gap.
  • a similar double ring could also be incorporated between the flanges of the housing parts 43 and 44. An improvement of operating efficiency can then be obtained at least at the blade ends by gap reduction.
  • the insertion of the rings also provides for a reverse flexure of the housing. That is, the housing, which is bent downwards at the ends solely by the influence of gravity, can be bent by the intermediate ring 6 so that the ends are conversely raised above the geometric axis.
  • the invention thus provides a simple and relatively inexpensive means for controlling the sag or deflection in a machine housing.
  • the double ring can be simply made and put in place in a simple manner.
  • the two parts of the ring are of varying thickness as shown in the drawings and can be made from identical pieces. Such pieces can be initially disposed in mating engagement with each other to form a single minimal thickness with the plane of the contact surfaces therebetween disposed at an angle to the plane of the exposed surfaces which are parallel to each other. Rotation of one ring with respect to the other causes the exposed planes to move from a parallel position to a position in which the planes are angularly disposed with respect to each other.
  • a ring disposed between said sections for changing the deflection of said sections from said axis in the plane of said ring, said ring comprising a pair of part-rings in bearing relation to each other and to a respective one of said housing sections, said partrings being of varying thickness to dispose the plane of division therebetween at an inclined angle relative to the contact planes thereof whereby the contact planes between each part ring and housing section can be adjusted relative to each other to a selective angle upon rotation of at least one of said rings.
  • each housing section includes a flange thereon bearing against a respective part ring, each said flange and each said part ring having a plurality of circumferentially spaced bores therein disposed about a pitch circle with uniform pitch to receive bolts for securing said sections and part-rings together.
  • each part-ring is divided into at least two annular segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00227431A 1971-03-17 1972-02-18 Deflection control means for machine housings Expired - Lifetime US3740164A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH441771A CH536456A (de) 1971-03-17 1971-03-17 Unter dem Eigengewicht sich elastisch deformierendes Maschinengehäuse

Publications (1)

Publication Number Publication Date
US3740164A true US3740164A (en) 1973-06-19

Family

ID=4275744

Family Applications (1)

Application Number Title Priority Date Filing Date
US00227431A Expired - Lifetime US3740164A (en) 1971-03-17 1972-02-18 Deflection control means for machine housings

Country Status (9)

Country Link
US (1) US3740164A (it)
JP (1) JPS5146202B1 (it)
CH (1) CH536456A (it)
DE (1) DE2114222C2 (it)
FR (1) FR2178274A5 (it)
GB (1) GB1378531A (it)
IT (1) IT950306B (it)
NL (1) NL148376B (it)
SE (1) SE368731B (it)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6571563B2 (en) * 2000-12-19 2003-06-03 Honeywell Power Systems, Inc. Gas turbine engine with offset shroud
US7726883B2 (en) 2004-07-01 2010-06-01 Elliott Company Four-bearing rotor system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4222708A (en) * 1978-06-26 1980-09-16 General Electric Company Method and apparatus for reducing eccentricity in a turbomachine
EP0646699B1 (de) * 1993-09-03 1998-04-22 Asea Brown Boveri Ag Verfahren zur Anpassung der Radialturbine eines Turboladers an eine Brennkraftmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE927782C (de) * 1952-01-12 1955-05-16 Licentia Gmbh Teilfugendichtung fuer Hoechstdruckdampf- oder Gasturbinen u. dgl.
US3556672A (en) * 1969-05-26 1971-01-19 Gen Electric Gas turbine support arrangement
US3594095A (en) * 1968-12-03 1971-07-20 Siemens Ag Casing for low-pressure stages of steam turbines of completely welded multishell construction
US3652178A (en) * 1968-11-28 1972-03-28 Bennes Marrel Device for the output shaft of a gas turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE927782C (de) * 1952-01-12 1955-05-16 Licentia Gmbh Teilfugendichtung fuer Hoechstdruckdampf- oder Gasturbinen u. dgl.
US3652178A (en) * 1968-11-28 1972-03-28 Bennes Marrel Device for the output shaft of a gas turbine
US3594095A (en) * 1968-12-03 1971-07-20 Siemens Ag Casing for low-pressure stages of steam turbines of completely welded multishell construction
US3556672A (en) * 1969-05-26 1971-01-19 Gen Electric Gas turbine support arrangement

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6571563B2 (en) * 2000-12-19 2003-06-03 Honeywell Power Systems, Inc. Gas turbine engine with offset shroud
US7726883B2 (en) 2004-07-01 2010-06-01 Elliott Company Four-bearing rotor system

Also Published As

Publication number Publication date
SE368731B (it) 1974-07-15
DE2114222C2 (de) 1973-04-19
FR2178274A5 (it) 1973-11-09
JPS5146202B1 (it) 1976-12-08
DE2114222B1 (de) 1972-09-21
IT950306B (it) 1973-06-20
NL148376B (nl) 1976-01-15
GB1378531A (en) 1974-12-27
CH536456A (de) 1973-04-30
NL7106159A (it) 1972-09-19

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Date Code Title Description
AS Assignment

Owner name: SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND, SWIT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR;REEL/FRAME:005221/0890

Effective date: 19890530