US2339779A - Liquid cooled, multiringed turbine rotor - Google Patents

Liquid cooled, multiringed turbine rotor Download PDF

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Publication number
US2339779A
US2339779A US229997A US22999738A US2339779A US 2339779 A US2339779 A US 2339779A US 229997 A US229997 A US 229997A US 22999738 A US22999738 A US 22999738A US 2339779 A US2339779 A US 2339779A
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United States
Prior art keywords
rotor
channels
blades
hub
bores
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Expired - Lifetime
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US229997A
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English (en)
Inventor
Holzwarth Hans
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HOLZWARTH GAS TURBINE CO
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HOLZWARTH GAS TURBINE CO
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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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor

Definitions

  • the present invention relates to the cooling of turbine rotors, and more particularly of rotors driven by combustion gases, such as gases generated by explosion of fuel and air under constant volume.
  • Radial bores through the rotor body have proved t'o be the only means suitable for the supplying of the cooling agent to and its withdrawal from the rotor crown or the blades,'such bores connecting distributing channels, directed for example at the feet of the blades along the blade-ring, with the hollow hub of the turbine rotor.
  • the cooling agent can flow outwardly through one or several radial bores to the Justmentioned distributing channels and can be withdrawn through other bores inwardly toward the wheel hub.
  • the .present invention accordingly is based uu-l on the discovery that all branching of the conduits for the .cooling agent, leading to the formation of dead spaces with reduced -fiow velocities, must be avoided, and thatin the case ot multi-ringed rotors. in spite of the increased expenditure of material and of manufacturing cost, straight bores through the body of the rotor,
  • liquid-cooled, multi-ringed turbine rotors which are free from bends and branches, must run from each of the distributing or collecting channels in the rotor, crown to the rotor hub. Consequently, liquid-cooled, multi-ringed turbine rotors, especially for explosion turbines, are characterized in accordance with the invention by the feature that the rotor is constructed of a plurality of individual rotor elements or discs. each having a crown sufiiciently wide for only one ring of blades.
  • the cooling agent conduits which connect the channels associated with each blade ring in the circumferential direction of the wheel and distribute the cooling agent to the individual blades, with the hollow hub oi the wheel being constructed as uninterrupted, straight and tubular passageways continuously from the cooled blade surfaces to the point of discharge into the hollow hub, such passageways for the different blade rings lying in separate planes trans-- verse to the shaft axis and intersecting the enlarged body of the rotor.
  • Fig. 1 illustrates a longitudinal section through the central axis of a rotor constructed in accordance with the invention, the section being taken generally along the line I-I of Fig. 3.
  • Fig. 2 shows that part of the rotor, on an enlarged scale, at which the radial cooling agent conduits open into the hollow hub, and is a section along the line II-II of Fig..3; while Fig. 3 shows on the scale of Fig. 2 a vertical cross-section through the rotor along the line "I, forged thereto, the rotor elements I, 3, 4 and 6 carrying respectively the rings of blades Ia, 3a, 4a and 6a.
  • the individual rotors I and 3, and likewise 4 and 6, are connected by welding at their circumferences at the places ⁇ indicated at 8 and 9, so that a closed, unitary rotating body is provided.
  • the rotor elements are preferably of the Laval type of wheels of uniform strength and thus are of reduced thickness below the crowns, but the solid body or web of the elements underlies each ring of blades down to the hub.
  • a series of channels and collecting spaces at the rotor hub are associated with the rotor sections 6, 4, 3 and nelbeing connected with the supply and discharge, more or less radial bores I0 and IUa.
  • the cooling agent enters at I2 into the cooling tube I3, arranged within a. bore in the shaft of larger diameter than the tube, and passes through the slits I4 into the annular space I5 which surrounds the other end of the tube I3. From this point the cooling agent reaches the distributing or collecting channels II of the rotor 6 through the radial bores Il), and is discharged from such channels through the radial bores Illa whence it passes into the channels I5.
  • the latter' run parallel to the axis of the shaft and are spaced circumferentially about the tube I3.
  • These channels I6 are formed by axially parallel and axially transverse ridges or ribs Ilia, there being a channel I6 for each discharge bore I0a of the rotor section 6.
  • each of the channels IS communicates with an inlet bore IIl of the rotor section 4, the discharge bores Illa of such rotor section leading from the distributing channels I l thereof and opening into the annular space I'lI between the pipe I3 and the walls of the shaft bore. From the other end of the space I] run the supply bores l0 for the distributing channels II of the rotor section 3, the discharge bores Illa in such section emptying into separate, circumferentially spaced axially parallel channels I'Ia formed by the axially parallel and axially transverse ridges or ribs IIb.
  • the present invention solves in a very simple mam ner the problem of providing a rotor having a plurality of rings of blades, with straight. unbranched supply'and discharge bores for the cooling agent distributing channels at the base of the blades despite the fact that the actual axial wall thickness of the web of the-rotor inwardly bf the crown is less than the axialthickness of the crown and in fact may be no greaterthan the distance between the center lines of the leftmost and rightmost rows of blades.
  • the web of reduced thickness is solidly constructed, broken or branched supply and discharge conduits I0, Illa are unavoidable.
  • an annular space 19a is provided between each two rotor sections, so that despite the reduced web thickness, web material exists continuously from each blade ring radially to the hub.
  • the rotor By. constructing the rotor as a composite member by welding together, at their peripheries, several individual rotors, the provision of the radial supply and discharge conduits and also the distributing channels in the crown or crowns of the rotor is greatly facilitated as these passageways can be formed in the individual rotor sections before they are united.
  • a construction of this kind leads to further advantages by reason of the fact that the wall thicknesses of the individual rotor sections turn out smaller than the wall thickness of a wheel carrying a plurality .of blade rings; in this way distortions of the rotors under the heat stresses are eilectively avoided. Also, the dimensions of the rotor hubs remain within tolerable limits, in particular sudden thickenings can be dispensed with.
  • the explosion chamber 36 is charged with air through the valve 36 and with gas or other fuel through the valve 3l;
  • the mixture is then ignited by the spark plugs A 38.
  • the nozzle ⁇ valve theni's opened under the control of a suitable timing device and discharges the hot gases at high pressures into an expansion nozzle which directs them against the blades.
  • a liquid-cooled, combustion gas turbine rotor comprising a plurality of rotor elements of uniform strength circumferentially united at the crown, each having a crown sumciently wide to receive only a single ring of blades, said elements being of reduced thickness immediately inside of said crown, whereby anannular space nels in each rotor element through the web of -the element and connecting the channels ⁇ sepa.-V
  • a liquid-cooled combustion gas turbine rotor comprising a plurality of circumferentially united individual rotor elements of uniform strength, a hollow hub connected to the rotor, each rotor element having a crown suiciently wide to receive only a single ring of blades and being of reduced thickness immediately inside of the said crown, whereby an annular space is formed between adjoining elements, the web extending radially continuously from the blade feet to the hub, separate distributing channels for a liquid cooling agent associated with the individual rings of blades and located in the crown of the .respective rotor elements, substantially straight, unbranched supply and discharge bores running through the web of the respective rotor element from each of said channels to the hub -of the rotor,v the bores for the d′′rentblade rings thus lying in different axially transverse planes, and supply and discharge channels for the cooling agent connected with said bores at the hub of the rotor and both opening at the sameside of the hub.
  • a liquid-cooled combustion gas turbine rotor having a plurality of axially traversed rings of blades thereon, a hollow hub forming part of the rotor, separate distributing channels for a liquid cooling agent associated with the individual rings of blades and located in the rotor, substantially straight, unbranched supply and discharge bores running through the body of the rotor between each of said channels and the hub of the rotor, the bores for the different blade rings lying in different axially transverse planes,
  • a liquid-cooled combustion gas turbine rotor having a plurality of axially traversed rings of blades thereon, a hollow hub connected with the rotor, separate distributing channels for a liquid cooling agent associated with the individual rings in series by way of said supply and discharge v 5.
  • a liquid-cooled combustion gas turbine rotor having a plurality of axially traversed rings of blades thereon, a hollow hub connected with the rotor, separate distributing channels for a liquid cooling agent associated with the individual rings of blades and located in the rotor,
  • a liquidi-cooled. combustion gas turbine rotor having a plurality of rings of blades thereon upon the same, axially continuous crown, a separate channel for a liquid cooling agent located in the rotor adjacent to the feet of blades in each ring and running in the circumferential direction and distributing the cooling agent to the individual blades-of the associatedring, a hollow hub forming part of the rotor, the body of the rotor being of reduced axial thickness inwardly of the crown and being divided into as many sections as there are rows of blades by the interposition of annular spaces between the sections, whereby solid web material extends radially continuously from said channels to the rotor hub, a pipe for cooling agent arranged within the hub in spaced relation to the' walls thereof and forming a surrounding,.reverse path for the cooling agent, and straight conduits passing through the rotor and connecting the channels separately with the hollow hub of the rotor, the inlet and discharge ends of theconduits at the hub being rounded off.
  • a liquid-cooled combustion gas turbine rotor comprising two end sections each having a single rotor element and a single blade ring thereon, and a stub shaft projecting from each element, and acentral section consisting of two spaced rotor elements joined by an intermediate shaft section and united to the aforementioned elements at the outer peripheries of said elements, the adjacent elements being of approximately the same outer diameter; said rotor elements eachhavinga crown suiiiciently wide to receive only a single ring of blades, vand being of reduced thickness immediately inside of said crown, channels for a liquid cooling agent located in each rotor element adjacent to the feet of blades in each ring, and'running in the circumferential direction and distributing the cooling agent to the individual blades, a hollow hub connected with the rotor and adapted to receive a cooling fluid, and straight bores running directly from the channels in each rotor element through the body of the element and connecting the channels separatelywith the hollow hub of the rotor.
  • a liquid-cooled, combustion gas turbine rotor having a hollow hub forming part thereof, a plurality of rings of blades on the crown of the rotor, channels for a liquid cooling agent located in th; rotor adjacent ⁇ to the feet of the blades in said rings of blades, the body of the rotor being of reduced actual thickness inwardly of the crown and being divided into as. many sections as there are rows of blades bythe interpositionof annular spaces between the sections, whereby,
  • solid web material extends radially continuously from said channels to the rotor hub, straight bores lying in such axially spaced web sections and connecting the channels with the interior ofthe hub, means within the hub forming axial channels between the bores associated with the channels of different blade rings, and means for supplying a cooling agent to and withdrawing the same from the hub at the same 'side of the hub.
  • a liquid-cooled, combustion gas turbine rotor having a hollow hub forming part thereof, a plurality of rings of blades on the crown of the rotor, channels for a liquid cooling agent located in the rotor adjacent to the feet of the blades in said rings of blades, the body of the rotor providing a continuous mass of metal from the feet of the blades of each of said rings radially to the rotor hub, straight, unbranched bores connecting the channels with the interior of the hub, means within the hub forming axial channels between the bores associated with the channels of different blade rings, means for supplying a cooling agent to and withdrawing the same from the hub, a plurality of channels being associated with each blade ring and the supply and discharge bores for each ring being arranged in alternation in a substantially radial plane and likewise in substantially axial planes from blade ring to blade ring, the cooling channels, axial channels and bores being so interconnected that tor having a hollow hub forming part thereof,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US229997A 1937-09-18 1938-09-15 Liquid cooled, multiringed turbine rotor Expired - Lifetime US2339779A (en)

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DE2339779X 1937-09-18

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FR (1) FR843481A (fr)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479056A (en) * 1944-08-23 1949-08-16 United Aircraft Corp Cooling turbine rotors
US2484955A (en) * 1946-02-19 1949-10-18 Westinghouse Electric Corp High-temperature fan
US2532721A (en) * 1944-08-23 1950-12-05 United Aircraft Corp Cooling turbine rotor
US2554368A (en) * 1944-08-23 1951-05-22 United Aircraft Corp Turbine rotor cooling
US2633327A (en) * 1946-03-01 1953-03-31 Packard Motor Car Co Gas turbine wheel with liquid cooling means
US2788951A (en) * 1951-02-15 1957-04-16 Power Jets Res & Dev Ltd Cooling of turbine rotors
US2815926A (en) * 1953-03-19 1957-12-10 Parsons & Marine Eng Turbine Cooling of gas turbine rotors
US2849210A (en) * 1953-01-19 1958-08-26 Gen Motors Corp Turbine blade cooling system
US2883152A (en) * 1953-01-19 1959-04-21 Gen Motors Corp Evaporative cooled turbine
US2920865A (en) * 1952-10-31 1960-01-12 Rolls Royce Bladed stator or rotor constructions with means to supply a fluid internally of the blades
US3110473A (en) * 1957-06-07 1963-11-12 Basf Ag Gas turbine plant and method of operating the same
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
US7677048B1 (en) * 2006-05-24 2010-03-16 Florida Turbine Technologies, Inc. Turbine last stage blade with forced vortex driven cooling air
US20150337733A1 (en) * 2014-05-23 2015-11-26 General Electric Company Cooling supply circuit for turbomachinery

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479056A (en) * 1944-08-23 1949-08-16 United Aircraft Corp Cooling turbine rotors
US2532721A (en) * 1944-08-23 1950-12-05 United Aircraft Corp Cooling turbine rotor
US2554368A (en) * 1944-08-23 1951-05-22 United Aircraft Corp Turbine rotor cooling
US2484955A (en) * 1946-02-19 1949-10-18 Westinghouse Electric Corp High-temperature fan
US2633327A (en) * 1946-03-01 1953-03-31 Packard Motor Car Co Gas turbine wheel with liquid cooling means
US2788951A (en) * 1951-02-15 1957-04-16 Power Jets Res & Dev Ltd Cooling of turbine rotors
US2920865A (en) * 1952-10-31 1960-01-12 Rolls Royce Bladed stator or rotor constructions with means to supply a fluid internally of the blades
US2849210A (en) * 1953-01-19 1958-08-26 Gen Motors Corp Turbine blade cooling system
US2883152A (en) * 1953-01-19 1959-04-21 Gen Motors Corp Evaporative cooled turbine
US2815926A (en) * 1953-03-19 1957-12-10 Parsons & Marine Eng Turbine Cooling of gas turbine rotors
US3110473A (en) * 1957-06-07 1963-11-12 Basf Ag Gas turbine plant and method of operating the same
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
US7677048B1 (en) * 2006-05-24 2010-03-16 Florida Turbine Technologies, Inc. Turbine last stage blade with forced vortex driven cooling air
US20150337733A1 (en) * 2014-05-23 2015-11-26 General Electric Company Cooling supply circuit for turbomachinery
US9719425B2 (en) * 2014-05-23 2017-08-01 General Electric Company Cooling supply circuit for turbomachinery

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Publication number Publication date
FR843481A (fr) 1939-07-04

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