US2821418A - Machine unit including a turbine and a machine driven thereby - Google Patents

Machine unit including a turbine and a machine driven thereby Download PDF

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Publication number
US2821418A
US2821418A US524559A US52455955A US2821418A US 2821418 A US2821418 A US 2821418A US 524559 A US524559 A US 524559A US 52455955 A US52455955 A US 52455955A US 2821418 A US2821418 A US 2821418A
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US
United States
Prior art keywords
turbine
wheel
machine
turbine wheel
bolt
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
US524559A
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English (en)
Inventor
Schacr Franz
Allemann Martin
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.)
Sulzer AG
Original Assignee
Sulzer 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
Application filed by Sulzer AG filed Critical Sulzer AG
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Publication of US2821418A publication Critical patent/US2821418A/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/20—Connections with hook-like parts gripping behind a blind side of an element to be connected
    • F16B2200/205—Connections with hook-like parts gripping behind a blind side of an element to be connected the hook being a separate retainer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a machine unit including a turbine and a machine driven by the turbine, more particularly to a unit consisting of a waste gas operated turbine and a compressor for supercharging an internal combustion engine.
  • the most delicate part of a unit or group of the type described above is the turbine wheel.
  • the latter is not only exposed to the high and variable temperatures and velocities of its operating medium but is also exposed to undesirable effects produced by the operating medium. If the operating medium is steam, it causes erosions, corrosions, and deposits. These efiects are more pronounced, if combustion gases are used as operating medium.
  • the blades of the turbine wheel may also be damaged by foreign objects carried along by the operating medium. Besides a reduction of the operating efficiency, the turbine wheel may become unbalanced so that serious destructions may occur unless the support of the turbine wheel is so Well constructed that it can sustain a multiple of the stresses to which it is exposed at normal operating conditions.
  • the turbine is supported by a bolt extending through a central bore in the wheel and pulling the turbine wheel at great initial tension against the end of the shaft of the machine which is driven by the turbine.
  • the turbine wheel is thus mounted in overhung fashion on the end of the shaft of the driven machine.
  • the end of the shaft of the driven machine is pref erably shaped like a bell against the rim of which the turbine wheel is pressed, the bolt extending through the turbine wheel abutting against the latter substantially in the same plane in which the wheel abuts against the rim of the flared end of the shaft of the driven machine.
  • the bolt may be secured to the turbine wheel by means of a lock ring surrounding the head of the bolt and being prevented from revolving therearound.
  • the lock ring may be received in a suitable axial recess in the hub of the turbine wheel and abutting against an internal shoulder in the hub of the wheel secured therein by means of a split ring.
  • the lock ring may be provided with protuberances extending into suitable radial recesses in the body of the turbine wheel for preventing relative rotation of the lock ring and of the turbine wheel.
  • the bolt is preferably provided with a collar having a greater outside diameter than the inner diameter of the split ring and being located at the side of the lock ring which is distal with respect to the split ring so that when the structure is disassembled, after removal of the split ring and of the lock ring and after preliminary loosening of the bolt, the split ring may be reinserted, the collar of the bolt now abutting against the split ring so that upon further unscrewing of the bolt, the collar of the latter presses against 2,821,418 Patented Jan. 28, 1958 ICC the split ring, forcing the turbine wheel away from the rim of the bell shaped end of the shaft of the driven machine.
  • Fig. 1 is a longitudinal sectional view of a turbine and of the bearing of a machine driven by and adjacent to the turbine;
  • Fig. 2 is an enlarged scale plan view of a lock ring used in the structure according to the invention.
  • Fig. 3 is an end view of an assembly according. to the invention for securing the central bolt for mounting the turbine wheel;
  • Fig. 4 is an axial sectional view of the system shown in Fig. 3; r
  • Fig. 5 is an axial sectional view of the system according to Figs. 3 and 4 arranged for separating the turbine wheel from the shaft of the driven machine.
  • Fig. 1 illustrates a portion of a machine group which is suitable for supercharging an internal combustion engine, not shown, and which includes a compressor, of which only one shaft bearing is shown,-and a waste gas turbine.
  • a partly shown annular chamber 1 formed in the easing of a waste or exhaust gas turbine receives the superatmospheric exhaust gas of the internal combustion engine and directs the gas along the arrows 2 between guide blades 3 from which the gas flows between the running blades 4 of a turbine wheel 5.
  • the gas leaving the turbine wheel flows between outlet guide or support blades 6 which are arranged in a difiusor 7.
  • the latter is connected with the turbine casing by means of a flange 8 and can be easily removed from the casing for exposing the outer surface of the turbine wheel 5.
  • the turbine wheel 5 is pulled by means of a pretensioned bolt 9 extending through a central bore of the turbine wheel against a compressor shaft 10 which extends beyond a bearing 11 outside of the compressor, the turbine wheel being connected with the compressor shaft in overhung fashion.
  • the end of the compressor shaft 10 is flared, forming a bell 12 against the rim 13 of which the turbine wheel 5 is pressed by the pretensioned bolt 9.
  • the diameter of the rim 13 is substantially one half of that of the wheel 5.
  • This structure forms a rigid and solid connection between the shaft 10 and the wheel 5. Since the wall thickness of the bell 13 can be made relatively small without impairing rigidity of the structure, the connection elastically yields in radial direction and throttles the heat flow from the turbine to the compressor.
  • the bearing 11 is protected against undesired heating by the turbine wheel 5.
  • the temperature of the rim 13 of the bell 12 is almost equal to that of the turbine wheel so that it will follow the changes of diameter of the turbine wheel 5 caused by heating of the wheel and by centrifugal forces.
  • the bolt 9 has a shoulder 14 abutting against a corresponding shoulder of the turbine wheel, transmitting the pull exerted by the bolt to the turbine wheel.
  • the shoulder 14 is substantially in the same plane as the rim 13 of the bell 12. Therefore axial expansion of the wheel 5 cannot change the pretension of the bolt 9.
  • the length of the bolt 9 is substantially equal to the thickness of the hub of the wheel 5 plus the longitudinal extension of the bell 12.
  • the thickness of the wall of the bell 12 changes in the axial direction so that the temperatures of the bell 3. and of the'b'olt 9drop in*tliesame manner in the direction away-from the-turbine-wheel and the temperaturedifferences between the bell andlthe bolt which may cause a change of the pretension of the belt are reduced to a minimum.
  • the b'olt 9 is' provided with locking means, shown in Figs. 2 to 4, whose parts can also be used for pressing theturbine wheel 'away from the bellrim, as shown in Fig. 5'.
  • a lock-ring 18, shown in Fig: 2' is axially movable but unrotatable on the headZZ-at the endof the bolt 9' and is held against slipping 01f the bolt head by means of a split ring 19, the latter being received in a suitable annular'rec'ess in' the turbine wheel' 51'
  • the lock ring 18 has radial projections extending into appropriate recesses- 20 in the turbine'wheel 5" for preventing rotation of'the lock ring relatively to the wheel.
  • the bolt 9 is provided with a collar 21 at the base of the bolt head (Fig. 4), the outer diameter of the collar- 21 being greater than the inner diameter of the split ring 19'.
  • the lock ring 18- is between the collar 21' and the split ring 19and there is a clearance between the collar 21 and the turbine wheel.
  • the split ring and the lock ring are removed, whereupon the split ring is reinserted and the bolt 9"is' loosened until the collar 21 abuts against the split ring 19.
  • the turbine wheel is pressed away'from'the rim 13-of the bell 12.
  • a machine unit including'a. turbine and a machine driven thereby comprising a turbine wheel having a. bore extending through the center of' said wheel, a shaft for the driven machine, a bolt screwed into the end of said shaft andf'extending through said bore, the end of said shaft. being flared to form a bell 'whose rim abuts against said turbine wheel, said bolt havinga shoulder, a shoulder in said here of said turbine wheel abuttingagainst the shoulder on said bolt for pressing said wheel against the rim of the bell shaped end of said shaft upon tightening of the bolt in said. wheel, said shoulders being in substantially the same plane as the rim of the bell shaped end of said shaft.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US524559A 1954-08-05 1955-07-26 Machine unit including a turbine and a machine driven thereby Expired - Lifetime US2821418A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH2821418X 1954-08-05

Publications (1)

Publication Number Publication Date
US2821418A true US2821418A (en) 1958-01-28

Family

ID=4572033

Family Applications (1)

Application Number Title Priority Date Filing Date
US524559A Expired - Lifetime US2821418A (en) 1954-08-05 1955-07-26 Machine unit including a turbine and a machine driven thereby

Country Status (6)

Country Link
US (1) US2821418A (fr)
CH (1) CH324034A (fr)
DE (1) DE964190C (fr)
FR (1) FR1127327A (fr)
GB (1) GB772121A (fr)
NL (1) NL86838C (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021105385A1 (fr) * 2019-11-29 2021-06-03 Siemens Aktiengesellschaft Procédé d'assemblage et de démontage d'un module de moteur à turbines à gaz et un ensemble pour celui-ci
US11226008B2 (en) * 2019-01-08 2022-01-18 Hamilton Sundstrand Corporation System and method for axially retaining two coaxial shaft components

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1112860B (de) * 1957-06-04 1961-08-17 Kloeckner Humboldt Deutz Ag Gasturbinenlaeufer
US4207035A (en) * 1977-12-27 1980-06-10 Cummins Engine Company, Inc. Turbocharger assembly
DE19518678C1 (de) * 1995-05-22 1996-10-31 Fichtel & Sachs Ag Anbindung eines Schwungrades an die Kurbelwelle

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2539387A (en) * 1945-08-17 1951-01-30 Timken Axle Co Detroit Vehicle wheel drive
US2577134A (en) * 1949-02-19 1951-12-04 Elliott Co Radial spline impeller drive for turbochargers

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE814545C (de) * 1949-04-29 1951-09-24 Ruston & Hornsby Ltd Mehrstufiger Laeufer fuer Axialturbinen, insbesondere Gasturbinen

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2539387A (en) * 1945-08-17 1951-01-30 Timken Axle Co Detroit Vehicle wheel drive
US2577134A (en) * 1949-02-19 1951-12-04 Elliott Co Radial spline impeller drive for turbochargers

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11226008B2 (en) * 2019-01-08 2022-01-18 Hamilton Sundstrand Corporation System and method for axially retaining two coaxial shaft components
WO2021105385A1 (fr) * 2019-11-29 2021-06-03 Siemens Aktiengesellschaft Procédé d'assemblage et de démontage d'un module de moteur à turbines à gaz et un ensemble pour celui-ci
CN114761666A (zh) * 2019-11-29 2022-07-15 西门子能源环球有限责任两合公司 组装和拆卸燃气涡轮发动机模块的方法以及组件
CN114761666B (zh) * 2019-11-29 2023-09-29 西门子能源环球有限责任两合公司 组装和拆卸燃气涡轮发动机模块的方法以及组件
US11773722B2 (en) 2019-11-29 2023-10-03 Siemens Energy Global GmbH & Co. KG Method of assembling and disassembling a gas turbine engine module and an assembly therefor

Also Published As

Publication number Publication date
GB772121A (en) 1957-04-10
FR1127327A (fr) 1956-12-13
DE964190C (de) 1957-05-16
CH324034A (de) 1957-08-31
NL86838C (fr) 1900-01-01

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