US2847184A - Bladed rotors and stators - Google Patents

Bladed rotors and stators Download PDF

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Publication number
US2847184A
US2847184A US345574A US34557453A US2847184A US 2847184 A US2847184 A US 2847184A US 345574 A US345574 A US 345574A US 34557453 A US34557453 A US 34557453A US 2847184 A US2847184 A US 2847184A
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United States
Prior art keywords
blades
rotor
discs
flanges
skirts
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Expired - Lifetime
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US345574A
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English (en)
Inventor
Islip Leonard
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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.)
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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
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3076—Sheet metal discs

Definitions

  • This invention relates to the construction of bladed rotors, for example, for axial flow turbines and more particularly for axial flow compressors.
  • the object of the invention is to provide a rotor construction which is cheap and light, and suitable for rapid mass production.
  • the construction is not necessarily intended to be suitable for use in steam and gas turbines intended for operation at high temperatures.
  • a further object of the invention is the provision of a stator construction which will similarly be cheap and light, and easy to make.
  • the invention provides a bladed rotor comprising a rotor element made up of at least one sheet metal disc having a peripheral flange, and a row of sheet metal blades mounted on said flange.
  • the blades are tubular and have their root ends flared out to form a lateral skirt seating on and secured to the rotor disc flange.
  • the rotor element is made up of two flanged sheet metal discs arranged back to back .and the blades are secured to the flanges of both discs.
  • the stator similarly comprises a sheet metal casing having a row of sheet metal blades attached thereto.
  • the stator blades are tubular and have their ends flared out to form skirts which seat on and are secured to the stator casing.
  • the stator casing is formed with holes into which the ends of the blades are inserted and the skirts are secured to the outer surface of the casing, and in another form, the skirts are seated upon and secured to the inner surface of the casing.
  • stator blades may be similarly formed with skirts for attachment to a shroud ring.
  • Figure l is an axial half-section of the outlet end of a multistage compressor rotor and stator.
  • Figure 2 is a fragmentary section on the line II-II in Figure 1.
  • Figure 3 is a fragmentary developed section on the line III-III in Figures 1 and 2.
  • Figure 4 is an axial half-section of the outlet end of a second multistage compressor rotor and stator.
  • Figure 5 is a fragmentary developed view on the line V-V in Figure 4.
  • the rotor comprises -a number of co-axial, axially spaced rotor elements, each of which is made up of two sheet metal discs 1, 2. These discs have their peripheries turned over to form a channelshaped rim, that is, they each have a cylindrical flange 1a, 2a of the same width around the discs and a radially inwardly projecting annular portion 1b, 2b. The two discs are fastened together back to back by rivets (as shown) or bolts, or by welding or brazing or the like.
  • Each blade is a length of tube of the required aerofoil cross-section and twisted if necessary as required by the design.
  • the tube is slit along its leading and trailing edges for a distance equal to about half the desired root spacing between adjacent blades, and the two separated parts thus formed are bent outwards from each other to form lateral skirts 3a extending approximately at right angles to the axis of the blade.
  • skirts seat upon the rotor disc flanges 1a and 2a, and they are cut to such a length that the skirts on adjacent blades abut with one another (as shown in Figures 2 and 3), and to such ⁇ an angle that the blades are thereby set at the desired spacing and stagger angle.
  • this strip is channel shaped, the base being of such a length that it just spans the flanges 1a, 2a of the rotor discs, while the sides 4a of the channel bear against the inturned portions 1b, 2b of the rotor discs.
  • the strip has its edges shaped in conformity to the profile of the blades on each side thereof, so that when placed in position it just fills the space between the blades as shown in Figure 3.
  • the strips on each side of each blade meet at the leading and trailing edges thereof.
  • the underside of the strips are bevelled along the edges to accommodate the fillets at the base of the blades.
  • the strips 4 and the blade skirts 3a are secured to the rotor flanges by countersunk rivets 5.
  • the side portions 4a of the reinforcing strips are also secured by rivets 6 to the in-turned portions 1b, 2b of rotor discs.
  • the reinforcing strips 4 thus reinforce the blades against centrifugal force and oppose the tendency for the fillets at the blade roots to ybe pulled out straight.
  • the blades are so disposed on the disc flanges that the radi-al plane in which the centrifugal loads act coincides with the joint face of the two rotor discs 1, 2, so that there will be no bending movements tending to bend the discs over in an axial direction.
  • the inturned parts 1b, 2b of the rotor discs reinforce the flanges 1a, 2b, and oppose the tendency for them to bell out under centrifugal force.
  • the strip 4b, on the left-hand disc is however as hereinafter described with reference to Fig. 4.
  • Adjacent rotor elements are separated by channel-section annular spacers 7, the flanges of which abut with the rotor elements.
  • the spacers are of such a width that a space is left between the rotor flanges for the stator blade shroud as will be described below.
  • a frusto conical bearer member 8 to which is attached, for example, by welding, a stub shaft 9 for support in bearings.
  • the bearer members 8, the rotor elements and spacer elements 7 are all threaded on to a number of (say eight) tie rods 10 symmetrically disposed around the rotor axis and extending the length of the rotor, and are held together by nuts 10a on the ends of the tie rods.
  • each rotor element When building up the rotor, each rotor element is first built up as a sub-assembly.
  • the two rotor discs 1, 2 are placed back to back and riveted or otherwise fastened together, and then the blades 3 and reinforcing strips 4 are attached to the rotor disc flanges 1a, 2a.
  • the rivets could be replaced by spot welding.
  • the built-np rotor elements, the spacers 7 and the bearer-members 8 are assembled by simply threading them in order on to the tie rods 10, and tightening up with the nuts 10a.
  • the spacers 7 can be reinforced against buckling whenI tightening up the nuts a by distance pieces 19 threaded on to the tie rods 10 and lying between the sides of the spacers.
  • the stator is made up of a number of axially abutting frustoconical sheet metal liner members 11, each carrying a row of tubular sheet metal stator blades 12.
  • the liner is formed with holes into each of which the end of a blade is inserted.
  • This blade end is formed with tabs 12a which, after the blade is inserted in the hole, are turned over at right angles to the blade and are brazed or welded to the outside ofthe liner.
  • the inner ends of the row of blades are joined by a sheet metal shroud ring 13, which is formed with holes into which the other ends ofthe stator blades fit.
  • the shroud rring is channel shaped in cross section; the upstream side 13a is somewhat longer than the downstream side 13b and co-operates with the inturned portion on the adjacent rotor disc to form a knife-edge seal preventing leakage around the shroud ring.
  • each row of blades is made up of two segments which t together around the rotor. For convenience in manufacture the row of blades might be divided into a greater number of segments.
  • the liners are enclosed by a sheet metal outer casing 14.
  • This casing is also split on a diametrical plane and is provided with axial flanges 15 along the split for bolting the two halves together ⁇ and with flanges 16 at each end for. attachment to the adjoining inlet and outlet ducts.
  • the casing is formed with circumferential corrugations 14a behind each row of stator blades, which serve to stiffen the casing and also to accommodate the tabs 12a whereby the blades are fastened to the liner.
  • the casing and liners taper towards the outlet end of the compressor to provide the necessary reduction in the cross-sectional area available for the air flow.
  • the rotor shown in Figure 4 is in general similar to that of Figure l, and the same reference numerals have been used for corresponding parts.
  • the rotor discs 1, -2 are formed with axially extending peripheral flanges 1a, 2a, but the outer ends of these flanges are not reinforced by iii-turned portions as in the first embodiment.
  • the hollow sheet metal blades have lateral skirts 3a seating upon the flanges 1a, 2a, and between each pair of adjacent blades there is a reinforcing strip 4b, which however difers from the reinforcing strip 4 of Figure l in that it is not of channel section but is merely a flat strip, the skirts, flanges and strips being welded-e. g.
  • the annular spacers 7 are channel shaped in section as before but t closely under the disc flanges. The spacers are somewhat wider than the combined width of the two disc flanges which overlap them, so that a circumferential recess is left between the ends of the flanges.
  • the rotor discs 1, 2 and spacers 7 are held together by rings of nuts 17 and bolts 18 symmetrically disposed around the rotor axis.
  • one blade is formed with an integral extension 3b which is bent over in a circumferential direction and has its end secured e. g. by welding or brazing to the tip of the adjacent blade.
  • the rotor discs shall be provided with any central apertures for access to the spaces between the rotor elements. Accordingly it is necessary to secure either the nuts 17 or bolts 18 to the spacers 7 be- 4 fore assembly.
  • the nuts 17 could be tack welded to the inside of flange of the spacer 7, registering with the holes therein, the adjoining discs and spacers brought into abutment therewith, and the bolts 18 inserted.
  • the stator is generally similar to that shown in Figure l. However in this embodiment, the liner members 11 and the shroud rings 13 are not formed with holes to receive the ends of the blades.
  • Each stator blade 12 is slit for a short distance at each end along the leading and trailing edges, and the separated portions so formed are bent over to form lateral skirts 12C and 12d. These skirts seat upon and are secured to, e. g. by welding or brazing, the inner surface of the liners 11 and the outer surface of the shroud rings 13.
  • the skirts of circumferentially adjacent blades will be cut such a length as to abut with one another and at such an angle that the stator blades are set at the stagger angle required by the design.
  • the shrouds 13 are simple curved sheet metal strips, which coincide with the above-mentioned recesses provided between the ends of the flanges on adjacent rotor elements.
  • Both the rotor and stator blades have been described above Vas being lengths of tube of the appropriate aerofoil cross-section. However they could be made from sheet material, bent to shape on a former and welded along the seam, for example, at the trailing edge, as shown at 3c in Figure 5. In this case the seam will be left unwelded at one or both ends as the case may be for a length corresponding to the width of the skirt or skirts, and a corresponding slit made in the leading edge.
  • the tips of the rotor blades are in any case left open;
  • Suitable materials for both the rotor and stator and the blades would be aluminium or magnesium alloy, provided the compressor is intended to operate only at fairly low temperatures. For higher temperatures, steel might be used. In some circumstances it may be convenient to make the rotor and stator from sheet steel while the 'blades are made of aluminium alloy or magnesium alloy sheet.
  • the construction of Fig. 4 with parts brazed or Welded together is intended for use with blades, discs and re-inforcirrg strips of steel, and these parts would be of steel if they be brazed or welded as in the left-hand unit of Fig. l, but these parts would be rivetted together if one ⁇ or more of them were made of one of the said alloys.
  • the discs 1 and 2 together form a wheel with a central web through which passes the line of action of the centrifugal force acting on the blades.
  • the torque is transmitted by members 7 in Fig. 4 and by these and rods 10 in Fig. l, so that in each case the inner part of each web is loaded only by the centrifugal force.
  • a bladed rotor comprising two coaxial sheet metal discs having central parts extending transversely to the rotor axis, ⁇ and having their peripheries bent over to form flanges extending away from one another in a generally axial direction; a row of outwardly extending tubular blades dispo-sed circumferentially around the rotor, each blade being of aerofoil cross-section and having a concave and a convex face and being formed at its root end with a skirt extending from at least one of said faces transversely to the blade axis and seating upon the outer surfaces of the flanges; a reinforcing strip superimposed upon a skirt of a blade the edge of the strip being shaped to fit closely against said face at its junction with the skirt; and means securing said strip and said skirt to the flange.
  • a bladed rotor comprising two coaxial sheet metal discs having central parts extending transversely to the rotor axis and having their peripheries bent over to form flanges extending away from one another in a generally axial direction; a row of outwardly extending tubular blades of aerofoil cross-section disposed circumferentially around the rotor, each blade having a concave and a convex face and being formed on each face at its root end with a skirt extending in a circumferential direction, said skirts seating upon the outer surface of the flanges and the edges of skirts on circumferentially adjacent faces of circumferentially adjacent blades abutting with each other; a reinforcing strip between each pair of circumferentially adjacent blades and superimposed upon the abutting skirts, the edges of the strip being shaped to fit closely against said faces at t-he junction with the skirts; and means securing said strips and said skirts to the anges.
  • a bladed rotor comprising two coaxial sheet metal discs having central parts extending transversely to the rotor axis and having their peripheries bent over to form firstly lianges extending away from one another in a generally axial direction and secondly inwardly extending portions at the outer ends of the anges; a row of outwardly extending tubular blades disposed circumferentially around the rotor, each blade being formed at its root end with a skirt extending in a circumferential direction on each side thereof, seating upon the outer surface of the anges and abutting at its edges with the edges of the skirts on the circumferentially adjacent blades; a channel section reinforcing strip between each pair of circumferentially adjacent blades, the base of the channel spanning the anges, being superimposed upon the abutting skirts of the blades and being shaped at its edges to rit closely against the blades at their root ends, and the sides of the channel bearing one against each of the inwardly extending portions of the
  • a bladed rotor comprising a wheel having a peripheral rim and two side surfaces; a row of outwardly extending tubular blades disposed circumferentially around the rotor, each blade being formed at its root end with a skirt extending in a circumferential direction on each side thereof, seating upon the rim of the wheel and abutting at its edges wit-h the edges of the skirts on the circumferentially adjacent blades; a channel section reinforcing -stn'p between each pair of circumferentially adjacent blades, the base of the channel spanning the rim of the wheel and being superimposed upon the abutting skirts of the blades and being shaped at its edges to lit closely against the blades at their root ends, and the sides of the channel bearing one against each of the sides of 6 the wheel; means securing the base of the channel and the skirts to the rim of the wheel; and means securing the sides of the channel to the sides of the wheel.
  • a bladed rotor comprising two coaxial sheet metal discs having central parts extending transversely to the rotor axis and having their peripheries bent over to form firstly anges extending away from one another in a generally -axial direction and secondly inwardly extending portions at the outer ends of the anges; a row of outwardly extending tubular blades disposed circumferentially around the rotor, each blade being formed at its root end with a skirt extending in a circumferential direction on each side thereof and seating upon the outer surfaces of the flanges; a channel section reinforcing strip between each pair of circumferentially adjacent blades, the base of the channel spanning the flanges and being superimposed upon the circumferentially adjacent skirts of the blades, and the sides of the channel bearing one against each of the inwardly extending portions of the discs; .means securing the base of said channel and said skirts to the anges; and means securing the sides of the channel to the inwardly

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US345574A 1952-04-02 1953-03-30 Bladed rotors and stators Expired - Lifetime US2847184A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB312358X 1952-04-02
GB231052X 1952-10-23

Publications (1)

Publication Number Publication Date
US2847184A true US2847184A (en) 1958-08-12

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US345574A Expired - Lifetime US2847184A (en) 1952-04-02 1953-03-30 Bladed rotors and stators

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US (1) US2847184A (it)
BE (1) BE518910A (it)
CH (1) CH312358A (it)
DE (1) DE1084273B (it)
FR (1) FR1077668A (it)
GB (1) GB718138A (it)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2976011A (en) * 1955-02-10 1961-03-21 Stalker Corp Fabricated bladed compressor wheels
US3067928A (en) * 1960-01-25 1962-12-11 Gen Motors Corp Lightweight engine
US3083947A (en) * 1960-03-03 1963-04-02 United Aircraft Corp Compressor spacer
US3189261A (en) * 1957-02-14 1965-06-15 Stalker Dev Company Bladed rotor for fluid machines
US20080095634A1 (en) * 2006-10-20 2008-04-24 Titan Tool, Inc. Multi-stage turbine using steel and aluminum blades
CN114932329A (zh) * 2022-04-21 2022-08-23 楚天科技股份有限公司 一种用于加工超重力纯化床定子和转子的方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0618991D0 (en) 2006-09-27 2006-11-08 Rolls Royce Plc A component for a gas turbine engine

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US770207A (en) * 1904-07-12 1904-09-13 Wilkinson Steam Turbine Company Elastic-fluid turbine-wheel.
GB190523922A (en) * 1905-11-20 1906-11-15 Brush Electrical Eng Improvements in or relating to Fluid Pressure Turbines.
US874398A (en) * 1904-05-14 1907-12-24 Sebastian Ziani De Ferranti Bladed turbine element.
US906400A (en) * 1905-12-15 1908-12-08 Sebastian Ziani De Ferranti Process for attaching turbine-blades to their carrying elements.
US1074691A (en) * 1911-03-20 1913-10-07 Robert S Hotz Turbine-wheel.
US1210978A (en) * 1913-10-09 1917-01-02 Charles Algernon Parsons Construction of turbine and like rotors.
US1603966A (en) * 1924-01-29 1926-10-19 Lorenzen Turbinen Ag Turbine rotor
US1773349A (en) * 1926-08-07 1930-08-19 Bothezat George De Fan
FR863755A (fr) * 1939-09-25 1941-04-09 Rateau Soc Roues à ailettes pour turbo-machines
US2315407A (en) * 1942-04-08 1943-03-30 Torrington Mfg Co Double inlet blower wheel
US2337619A (en) * 1941-04-14 1943-12-28 Hydraulic Brake Co Blade wheel
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
US2405190A (en) * 1943-03-05 1946-08-06 Peerless Turbine Corp Fluid turbine
US2435427A (en) * 1946-09-16 1948-02-03 United Specialties Co Turbine wheel
FR992645A (fr) * 1944-07-22 1951-10-22 Rateau Soc Roue de turbomachines de grandes dimensions
US2601969A (en) * 1946-01-25 1952-07-01 United Specialties Co Turbine wheel
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
US2649243A (en) * 1948-08-05 1953-08-18 Edward A Stalker Axial flow compressor construction
US2678537A (en) * 1949-03-12 1954-05-18 Edward A Stalker Axial flow turbine type hydraulic torque converter
US2772851A (en) * 1950-06-14 1956-12-04 Stalker Dev Company Rotor construction
US2786646A (en) * 1949-08-10 1957-03-26 Power Jets Res & Dev Ltd Bladed rotors for axial flow turbines and similarly bladed fluid flow machines

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE442194C (de) * 1927-03-22 Lorenzen G M B H C Schaufelbefestigung fuer Gasturbinen
US2596781A (en) * 1945-12-29 1952-05-13 Moore Co Fan
DE897749C (de) * 1951-10-16 1953-11-23 Carl Kaelble Aus Blechen hergestellter Schraubenluefter

Patent Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US874398A (en) * 1904-05-14 1907-12-24 Sebastian Ziani De Ferranti Bladed turbine element.
US770207A (en) * 1904-07-12 1904-09-13 Wilkinson Steam Turbine Company Elastic-fluid turbine-wheel.
GB190523922A (en) * 1905-11-20 1906-11-15 Brush Electrical Eng Improvements in or relating to Fluid Pressure Turbines.
US906400A (en) * 1905-12-15 1908-12-08 Sebastian Ziani De Ferranti Process for attaching turbine-blades to their carrying elements.
US1074691A (en) * 1911-03-20 1913-10-07 Robert S Hotz Turbine-wheel.
US1210978A (en) * 1913-10-09 1917-01-02 Charles Algernon Parsons Construction of turbine and like rotors.
US1603966A (en) * 1924-01-29 1926-10-19 Lorenzen Turbinen Ag Turbine rotor
US1773349A (en) * 1926-08-07 1930-08-19 Bothezat George De Fan
FR863755A (fr) * 1939-09-25 1941-04-09 Rateau Soc Roues à ailettes pour turbo-machines
US2337619A (en) * 1941-04-14 1943-12-28 Hydraulic Brake Co Blade wheel
GB572859A (en) * 1942-04-03 1945-10-26 Armstrong Siddeley Motors Ltd Mounting the blades of axial-flow, rotary compressors or turbines
US2315407A (en) * 1942-04-08 1943-03-30 Torrington Mfg Co Double inlet blower wheel
US2405190A (en) * 1943-03-05 1946-08-06 Peerless Turbine Corp Fluid turbine
FR992645A (fr) * 1944-07-22 1951-10-22 Rateau Soc Roue de turbomachines de grandes dimensions
US2601969A (en) * 1946-01-25 1952-07-01 United Specialties Co Turbine wheel
US2435427A (en) * 1946-09-16 1948-02-03 United Specialties Co Turbine wheel
US2649278A (en) * 1948-07-15 1953-08-18 Edward A Stalker Rotor construction for fluid machines
US2649243A (en) * 1948-08-05 1953-08-18 Edward A Stalker Axial flow compressor construction
US2678537A (en) * 1949-03-12 1954-05-18 Edward A Stalker Axial flow turbine type hydraulic torque converter
US2786646A (en) * 1949-08-10 1957-03-26 Power Jets Res & Dev Ltd Bladed rotors for axial flow turbines and similarly bladed fluid flow machines
US2772851A (en) * 1950-06-14 1956-12-04 Stalker Dev Company Rotor construction

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2976011A (en) * 1955-02-10 1961-03-21 Stalker Corp Fabricated bladed compressor wheels
US3189261A (en) * 1957-02-14 1965-06-15 Stalker Dev Company Bladed rotor for fluid machines
US3067928A (en) * 1960-01-25 1962-12-11 Gen Motors Corp Lightweight engine
US3083947A (en) * 1960-03-03 1963-04-02 United Aircraft Corp Compressor spacer
US20080095634A1 (en) * 2006-10-20 2008-04-24 Titan Tool, Inc. Multi-stage turbine using steel and aluminum blades
CN114932329A (zh) * 2022-04-21 2022-08-23 楚天科技股份有限公司 一种用于加工超重力纯化床定子和转子的方法
CN114932329B (zh) * 2022-04-21 2023-12-22 楚天科技股份有限公司 一种用于加工超重力纯化床定子和转子的方法

Also Published As

Publication number Publication date
GB718138A (en) 1954-11-10
DE1084273B (de) 1960-06-30
CH312358A (de) 1955-12-31
BE518910A (it)
FR1077668A (fr) 1954-11-10

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