US2743080A - Turbine rotors - Google Patents

Turbine rotors Download PDF

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Publication number
US2743080A
US2743080A US158233A US15823350A US2743080A US 2743080 A US2743080 A US 2743080A US 158233 A US158233 A US 158233A US 15823350 A US15823350 A US 15823350A US 2743080 A US2743080 A US 2743080A
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United States
Prior art keywords
platforms
blade
blades
turbine
axial
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
US158233A
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English (en)
Inventor
Feilden Geoffrey Bertra Robert
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.)
Ruston and Hornsby Ltd
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Ruston and Hornsby Ltd
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Filing date
Publication date
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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
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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

Definitions

  • This invention relates to rotors of axial flow turbines having two or more stages, with especial reference to rotors for gas turbines.
  • the turbine rotor blades are usually mounted in the rims of the turbine wheels by means of serrated roots, sometimes known as fir trees, and the invention makes use of this type of construction.
  • the axial widths of they rims of mutually adjacent turbine wheels or discs are greater than the axial widths of the blades mounted in them so that the serrations at the roots of the blades do not occupy the whole axial length of the serrated slots in the rims of the wheels; and the gap between mutually adjacent wheel rims is filled by dummy platforms corresponding in number to the blades in each wheel and having serrated roots supported at each end in the parts of the serrated slots of the adjacent wheel rims unoccupied by the blade roots.
  • the surfaces of these platforms may be shaped to an arc struck from the axis of the turbine shaft so that when assembled they form a complete ring flush with the blade platforms of the adjacent turbine wheels.
  • the outer surfaces of the platice forms may be left fiat, in which case the complete ring pletely close, thus ensuring that the dummy platforms,
  • a further object of the invention is the provision of adequate cooling of the opposed faces of mutually adjacent turbine wheels or discs, when the space between their rims is filled by a substantially continuous ring of dummy platforms.
  • each of the dummyplatforms isv provided with a small slot or'notch .at or near one corner providing an opening between itand the nextdummy platform through which cooling air, fed into the space between the mutually adjacent turbine wheels for cooling the latter, can escape.
  • the escaping air forms a layer of cooling air over the blade roots and blade platforms of the blade-row downstream of the ring of dummy platforms.
  • the outer faces of the wheels carrying the first and last stages of blading are air-cooledin the usual way, the air escaping through the'clearance between the nozzle ring and the first row of moving blading and the clearance between the last row of moving blading and the exhaust cone; and the air escaping through the first of these clearances cools the platforms and inner ends of the blades of the firststage of rotorblading. Furthermore, the circulation of air through the spaces between mutually adjacent turbine wheels serves to cool the underfaces of the dummy platforms themselves.
  • Figure l is an axial section of a two-stage axial flow turbine rotor
  • Figure 2 is a broken plan view taken in the direction of arrow 2 of Figure l;
  • FIG 3 is a section on the line 3--3 of Figure 1 of a blades 18.
  • the blade roots 17 18 are of fir-tree form (see Figure 4) and each blade includes an integral platform 17 or 18
  • the rims 10 and 11 of the discs 10, 11 are axially slotted at lb 11 ( Figure 2) to receive the fir-tree blade roots.
  • Each disc has an equal number of blades and the blade roots 17 18 and the slots 10*, 11 are of the same fir-tree section, the slots 10, 11 being in mutual register circumferentially, i. e. so that when viewed endwise, each slot 10 exactly coincides with a slot 11.
  • the two turbine discs 10, 11 are axially spaced at their peripheryby gaps corresponding approximately to the axial width of the blades.
  • the blade-platforms 17 are substantially contiguous cireumferentially, and so are the blade-platforms 18 just suflicient clearance being allowed between them to allow for -expansion, so that the blade-platforms of each row of blades-presents a continuous annular drum-shaped surface.
  • the axial gap between'thesesurfaces isfilled by a row ofdummy platforms 19 havingfir-tree roots 19 which are exactly similar tothose of the blades and are inserted into -the"open or unfilledends of'the slots 10, 11
  • the dummy platforms 19 substantially fill the gap between'the bl'ade platforms 17 18 and-are substantially contiguous circumferentially, just sufiicient clearance both axially and circumferentially being provided to-allow for expansion.
  • This method of constructing the part of the inner wall of the turbine annulus intermediate between mutually adjacent rows of blade-platforms avoids the imposition of additional thermal stresses on the discs, the elements comprising the intermediate part of the annulus-wall itself being also substantially free from thermal stressing.
  • blade-supporting discs having axially enlarged hubs secured together and having rims axially spaced apart, a row of blades on each disc, each blade having a fir-trce root and a blade platform and the rims of the discs having axially extending fir-tree slots receiving the blade roots, the blade platforms of each row being substantially contiguous circumferentially and the platforms and roots of the bladesin each row being narrower axially than the axial width of thedisc rims and their fir-tree slots, and a row of dummy platforms having fir-tree roots, the ends of whichare supportedinthe fir-tree slots of mutually adjacent discs, the blade platforms and the dummy platforms being located entirelybeyond theouter peripheries of the disc rims, the dummy platforms being substantially contiguous circumferentially and substantially filling the axial gap between mutually adjacent rows of blade platforms so that the blade platforms and dummy platforms

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US158233A 1949-04-29 1950-04-26 Turbine rotors Expired - Lifetime US2743080A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB284189X 1949-04-29

Publications (1)

Publication Number Publication Date
US2743080A true US2743080A (en) 1956-04-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US158233A Expired - Lifetime US2743080A (en) 1949-04-29 1950-04-26 Turbine rotors

Country Status (4)

Country Link
US (1) US2743080A (de)
CH (1) CH284189A (de)
GB (1) GB667194A (de)
NL (1) NL72215C (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3692429A (en) * 1971-02-01 1972-09-19 Westinghouse Electric Corp Rotor structure and method of broaching the same
US3745628A (en) * 1971-07-29 1973-07-17 Westinghouse Electric Corp Rotor structure and method of construction
US3894324A (en) * 1971-08-14 1975-07-15 Motoren Turbinen Union Rotor for fluid flow machines
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US5031400A (en) * 1988-12-09 1991-07-16 Allied-Signal Inc. High temperature turbine engine structure
US5350276A (en) * 1992-04-17 1994-09-27 Gec Alsthom Electromecanique Sa High pressure modules of drum rotor turbines with admission of steam having very high characteristics
EP2546461A1 (de) * 2011-07-11 2013-01-16 General Electric Company Rotor-Baugruppe und zugehöriges Gasturbinenkraftwerk
US20150023785A1 (en) * 2013-07-19 2015-01-22 Michael J. Stanko Coupling for directly driven compressor
CN107269316A (zh) * 2017-08-17 2017-10-20 中南大学 一种燃气轮机中心拉杆式转子的锥形轮盘结构
US10385861B2 (en) * 2012-10-03 2019-08-20 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
US10443603B2 (en) * 2012-10-03 2019-10-15 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2901214A (en) * 1954-04-12 1959-08-25 Arthur J Slemmons Turbine wheel and shaft assembly
DE1044527B (de) * 1955-07-16 1958-11-20 Canadian Patents Dev Vorrichtung zur Verbindung einer hohlen Turbinenwelle, insbesondere bei einem Gasturbinentriebwerk mit einem frei tragend angeordneten Turbinenlaufrad
FR2295226A1 (fr) * 1974-12-16 1976-07-16 Europ Turb Vapeur Dispositif de clavetage entre disques d'une turbine
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB319622A (en) * 1928-09-24 1930-12-18 Vladimir Kalabek Gas turbine
US2430185A (en) * 1946-07-25 1947-11-04 Continental Aviat & Engineerin Turbine rotor
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US2461402A (en) * 1944-10-06 1949-02-08 Power Jets Res & Dev Ltd Rotor for multistage axial flow compressors and turbines
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB319622A (en) * 1928-09-24 1930-12-18 Vladimir Kalabek Gas turbine
US2461402A (en) * 1944-10-06 1949-02-08 Power Jets Res & Dev Ltd Rotor for multistage axial flow compressors and turbines
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor
US2430185A (en) * 1946-07-25 1947-11-04 Continental Aviat & Engineerin Turbine rotor
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3692429A (en) * 1971-02-01 1972-09-19 Westinghouse Electric Corp Rotor structure and method of broaching the same
US3745628A (en) * 1971-07-29 1973-07-17 Westinghouse Electric Corp Rotor structure and method of construction
US3894324A (en) * 1971-08-14 1975-07-15 Motoren Turbinen Union Rotor for fluid flow machines
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US5031400A (en) * 1988-12-09 1991-07-16 Allied-Signal Inc. High temperature turbine engine structure
US5350276A (en) * 1992-04-17 1994-09-27 Gec Alsthom Electromecanique Sa High pressure modules of drum rotor turbines with admission of steam having very high characteristics
EP2546461A1 (de) * 2011-07-11 2013-01-16 General Electric Company Rotor-Baugruppe und zugehöriges Gasturbinenkraftwerk
US10385861B2 (en) * 2012-10-03 2019-08-20 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
US10443603B2 (en) * 2012-10-03 2019-10-15 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
US10519962B2 (en) 2012-10-03 2019-12-31 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
US10533564B2 (en) 2012-10-03 2020-01-14 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
US10533565B2 (en) 2012-10-03 2020-01-14 Praxair Technology, Inc. Method for compressing an incoming feed air stream in a cryogenic air separation plant
CN105378316A (zh) * 2013-07-19 2016-03-02 普莱克斯技术有限公司 用于直接驱动的压缩机的联接件
US9371835B2 (en) * 2013-07-19 2016-06-21 Praxair Technology, Inc. Coupling for directly driven compressor
CN105378316B (zh) * 2013-07-19 2019-03-01 普莱克斯技术有限公司 用于直接驱动的压缩机的联接件
US20150023785A1 (en) * 2013-07-19 2015-01-22 Michael J. Stanko Coupling for directly driven compressor
CN107269316A (zh) * 2017-08-17 2017-10-20 中南大学 一种燃气轮机中心拉杆式转子的锥形轮盘结构

Also Published As

Publication number Publication date
NL72215C (de)
CH284189A (de) 1952-07-15
GB667194A (en) 1952-02-27

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