US3010643A - Axial flow compressors - Google Patents

Axial flow compressors Download PDF

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Publication number
US3010643A
US3010643A US627395A US62739556A US3010643A US 3010643 A US3010643 A US 3010643A US 627395 A US627395 A US 627395A US 62739556 A US62739556 A US 62739556A US 3010643 A US3010643 A US 3010643A
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US
United States
Prior art keywords
discs
chambers
rotor
pressure
slots
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
US627395A
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English (en)
Inventor
Ricketts Charles Pe Langworthy
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.)
Bristol Siddeley Engines Ltd
Original Assignee
Bristol Siddeley Engines 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.)
Filing date
Publication date
Application filed by Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
Application granted granted Critical
Publication of US3010643A publication Critical patent/US3010643A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F01D5/02—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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • AXIAL FLOW coMPREssoRs Filed Deo. 1o, 1956 2 sheets-sheet 2 portions of the bolts being reduced to a clearance diameter.
  • a number of dowels 65 are inserted in circumferentially spaced holes 66 in the anges, the holes extending axially of the rotor.
  • the blades 10.carried by the discs 11, 12, 21, 22, 23, 24 and 25 are provided with lir tree roots 33 which lit into corresponding tir tree slots 34 in the rim of each disc in known manner.
  • Suitably flanged rings such as 35 are disposed between the peripheries of adjacent bladecarrying discs in coaxial relation therewith to define the inner cylindrical surface of the working air passage between Ithe blades. between the discs and consequently air from the working air passage can creep into the annular chambers enclosed between these rings and the flanges 12a, 21a, 21b, 22a, 23a, 22b, 23b and 24a constituting the drum of the discand drum structure.
  • the rings '35 are prevented from rotating relatively to the discs by dowels 67.
  • 'Ihe shaft 60 has a frusto-conical end 36 provided with a flange 37 by which it is attached tothe rear end of the drum structure by the bolts 29 and the nuts 31.
  • Each of the blade-carrying discs is formed with a central bore 38 surrounded by a thickened hub portion.
  • a tubular member 39 having an outwardly-directed ange 40 at its forward end and an inwardly-directed ange 41 lat its rearwardrend is interposed between the blade-carrying discs 12 and 21, the ange 40 being secured to the discs y11 and 12 and to the spigot 13 by the bolts 16 and the tlange 41 being secured to the disc 21 by nuts 43 and bolts 44 which pass through holes 45 in the ilange 41 and through aligning holes 46 in the thickened hub p0rtion of -the disc 21 at a lesser radius than the bolts 16.
  • the tubular member 39 strengthens the forward end of the rotor and forms part of means for resisting deection of the discs bounding separate chambers in the rotor under the action of unbalanced endwise pressure load on the discs as ywill hereinafter be fully described.
  • the tubular member 39 also serves as part of a passage means or duct system for conveying air compressed in the compressor of which the rotor is lto form a part to a labyrinth seal (not shown) associated with the bearing 14, where the air is used for oil sealing and cooling purposes.
  • the duct system further comprise a tubular member 47 itted in the bores 38 of the discs 21 and 22, a tubular member 68 fitted in the bores 38 of the discs 22 and 23 and three equally spaced tubes 52 extending radially from hollow bosses 50 provided on the ltubular member 68 through holes 54 in the flange 23a to ports 69 in the Vlring 35 constituting the inner boundary of the working air passage between the fourth and fifth rows of blades.
  • the tubular member 68 is closed at Iits rearward end so Ithat air under pressure from between the fourth and fifth rows of blades is constrained to pass inwardly through the tubes 52 and ythen forwardly through the tubular members 68, 47 and 39 to the space within theV axial extensions 11b and 12b of the discs 11 and 12. From here the air passes outthrough openings 55 in the flange of the spigot 13- to the labryinth structure (not shown). Itwill be seen that this duct system dividesthe space within the drum structure into four separate chambers each of which is partly bounded by one or more of the discs and partly boundedby the anges constituting the drum structure.
  • these chambers are firstly 70, bounded by the discs 12 and 21 and the anges 12a and 21a, secondly 71, bounded by the discs 21 and 22 and the anges 21b and 22a, thirdly 72, bounded by the discs 22 and 23- and the flanges 22b and 23a, and fourthly 73 bounded by the disc 23 and the anges 23b and 24a,
  • This last chamber is in communication through the central openings 38 of the discs 24 and 25 with the hollow interior of the shaft 60.
  • passage means are provided from each of the chambers 70, 71, 72 and 73 through the drum structure constituted by the flanges 12a, 21a, 21b, 22a, 22b, 23a, 23b and 24a to the working air passage of the compressor.
  • these passages means take the form of shallow flat-bottomed slots 74 cut in the abutment faces of the flanges, at the interfaces 61, 62, 63 and 64, there being for example three such slots equally distributed around the abutment -face of each ange.
  • the slots in the opposed faces are in alignment with one another as shown in HGURE 3 to form elongated holes.
  • slots also provide a convenient way of facilitating the separation of the discs during dismantling of -the rotor for overhaul by the driving in of wedge-shaped tools, the fact that the slots are opposite one another and flat bottomed enabling this to be done with minimum danger of damaging the abutment faces of the anges.
  • holes 75 are provided inthe rings 35 opposite each of the slots 74. As already mentioned, the rings 35 are not normally so tightly fitting as to prevent all flow of air from the working air passage to the surface of the drum and thence through the slots 74, but nevertheless the holes 75 ensure that such cornmunication is maintained.
  • the existence of lthe slots 74 ensures that the pressures in the ⁇ chambers 70, 71, 72 and 73 will be graded in accordance with the stage by stage rise of pressure through the compressor and consequently the unbalanced endwise pressure loading on the discs 21, 22 and 23 is always towards the forward end of the rotor.
  • the tubular members 47 and 68 are provided at each end with shoulders 49 which bear against the sides of the hub portions of the discs 21, 22 and 23 and consequently the unbalanced endwise pressure loads on lthe discs 22 and 23 are transmitted to the disc 21.
  • Slots similar to those shown at 74 may also be provided in the abutment faces of the ⁇ discs 24 and 25 and of a labyrinth seal member 76 to facilitate separation of these parts.
  • Such slots admit to the chamber 73 supplies of air from between the sixth and seventh blade rows and from the outlet of the compressor but the pressure in the chamber 73 is not necessarily raised sincel air is drawn oi from this chamber from the rear end of the shaft 60 for cooling the turbine part of the rotor.
  • a rotor drum for a multi-stage axial flow compressor comprising a plurality of axially spaced discs having opposed axial extending portions engaging each other, pairs of adjacent discs and axially opposed portions defining closed chambers, said portions defining the outer periphery of each of the closed chambers of a plurality of successive closed chambers, an annular ring of blades carried by each of the said discs on the periphery thereof, a venting passage from each of said chambers through said portions communicating each of said chambers with the flow stream ⁇ between the downstream and upstream faces of each pair of adjacent rings of blades, one of said blade-carrying discs being at the low pressure end of the rotor, the chamber between said low pressure blade-carrying disc and the next higher blade-carrying disc being the lowest pressure chamber and successive chambers toward the higher pressure end of the rotor being progressively higher pressure chambers, said blade-carrying discs having central apertures therein, tubular members dening the inner walls of said successive closed cham ⁇

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US627395A 1955-12-23 1956-12-10 Axial flow compressors Expired - Lifetime US3010643A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB350066X 1955-12-23
GB61256X 1956-12-06

Publications (1)

Publication Number Publication Date
US3010643A true US3010643A (en) 1961-11-28

Family

ID=26240456

Family Applications (1)

Application Number Title Priority Date Filing Date
US627395A Expired - Lifetime US3010643A (en) 1955-12-23 1956-12-10 Axial flow compressors

Country Status (5)

Country Link
US (1) US3010643A (enrdf_load_stackoverflow)
CH (1) CH350066A (enrdf_load_stackoverflow)
DE (1) DE1072351B (enrdf_load_stackoverflow)
FR (1) FR1169048A (enrdf_load_stackoverflow)
GB (1) GB804007A (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3249293A (en) * 1964-01-23 1966-05-03 Gen Electric Ring-drum rotor
US3597109A (en) * 1968-05-31 1971-08-03 Rolls Royce Gas turbine engine axial flow multistage compressor
ITMI20100684A1 (it) * 2010-04-21 2011-10-22 Nuovo Pignone Spa Rotore impilato con tirante e flangia imbullonata e metodo

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4102603A (en) * 1975-12-15 1978-07-25 General Electric Company Multiple section rotor disc
FR2491549B1 (fr) 1980-10-08 1985-07-05 Snecma Dispositif de refroidissement d'une turbine a gaz, par prelevement d'air au niveau du compresseur

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1003321A (en) * 1909-01-27 1911-09-12 Giuseppe Belluzzo Steam-turbine.
US1008531A (en) * 1910-11-19 1911-11-14 Charles G Curtis Marine steam-turbine.
US2528635A (en) * 1943-06-22 1950-11-07 Rolls Royce Power gas generator for internalcombustion power units
US2583875A (en) * 1948-09-22 1952-01-29 Svenska Turbinfab Ab Rotor for axial flow elastic fluid compressors or turbines
US2610786A (en) * 1946-06-25 1952-09-16 Gen Electric Axial flow compressor
US2639885A (en) * 1950-03-23 1953-05-26 United Aircraft Corp Rotor construction for compressors and turbines
US2650017A (en) * 1948-11-26 1953-08-25 Westinghouse Electric Corp Gas turbine apparatus
FR1057171A (fr) * 1951-04-18 1954-03-05 Bristol Aeroplane Co Ltd Perfectionnements aux rotors pour compresseurs ou turbines à écoulement axial
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors
US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1003321A (en) * 1909-01-27 1911-09-12 Giuseppe Belluzzo Steam-turbine.
US1008531A (en) * 1910-11-19 1911-11-14 Charles G Curtis Marine steam-turbine.
US2528635A (en) * 1943-06-22 1950-11-07 Rolls Royce Power gas generator for internalcombustion power units
US2610786A (en) * 1946-06-25 1952-09-16 Gen Electric Axial flow compressor
US2583875A (en) * 1948-09-22 1952-01-29 Svenska Turbinfab Ab Rotor for axial flow elastic fluid compressors or turbines
US2650017A (en) * 1948-11-26 1953-08-25 Westinghouse Electric Corp Gas turbine apparatus
US2639885A (en) * 1950-03-23 1953-05-26 United Aircraft Corp Rotor construction for compressors and turbines
US2742224A (en) * 1951-03-30 1956-04-17 United Aircraft Corp Compressor casing lining
FR1057171A (fr) * 1951-04-18 1954-03-05 Bristol Aeroplane Co Ltd Perfectionnements aux rotors pour compresseurs ou turbines à écoulement axial
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3249293A (en) * 1964-01-23 1966-05-03 Gen Electric Ring-drum rotor
US3597109A (en) * 1968-05-31 1971-08-03 Rolls Royce Gas turbine engine axial flow multistage compressor
ITMI20100684A1 (it) * 2010-04-21 2011-10-22 Nuovo Pignone Spa Rotore impilato con tirante e flangia imbullonata e metodo
US8967960B2 (en) 2010-04-21 2015-03-03 Nuovo Pignone, S.P.A. Stack rotor with tie rod and bolted flange and method
RU2551453C2 (ru) * 2010-04-21 2015-05-27 Нуово Пиньоне С.п.А. Многоступенчатый ротор со стяжным стержнем и фланцем, закрепленным при помощи болтов, и способ сборки
EP2381109A3 (en) * 2010-04-21 2017-11-22 Nuovo Pignone S.p.A. Rotor stack for centrifugal compressor

Also Published As

Publication number Publication date
FR1169048A (fr) 1958-12-19
GB804007A (en) 1958-11-05
DE1072351B (enrdf_load_stackoverflow)
CH350066A (de) 1960-11-15

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