US2738126A - Construction of compressor rotors - Google Patents

Construction of compressor rotors Download PDF

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Publication number
US2738126A
US2738126A US256475A US25647551A US2738126A US 2738126 A US2738126 A US 2738126A US 256475 A US256475 A US 256475A US 25647551 A US25647551 A US 25647551A US 2738126 A US2738126 A US 2738126A
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United States
Prior art keywords
discs
disc
axially
ring
extending
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Expired - Lifetime
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US256475A
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English (en)
Inventor
Reginald G A Edwards
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
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    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • 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
    • F04D29/26—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
    • 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
    • F04D29/322—Blade mountings
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods

Definitions

  • a bladed compressorrotor comprises a plurality of discs most of which have an axially-extending peripheral portion which forms a shroud between two adjacent blade rows of the rotor and the axial extremity of which has a spigotal engagement with the next disc, the two discs jointly providing a radial-locating peripheral groove, for the roots of a blade row, when bolted together, radially inwardly of a the roots of' that row, through their spigotally-engaging portions.
  • bolt is used herein in a generic sense to include the use of screws, nuts and bolts, nuts and studs or the like.
  • all the discs may beas aforesaid, except for the end ones.
  • the two end discs are of steel and fast with shaft portions journalled in a diaphragm or other portion of the stator, and all the other discs, which may be of aluminium or other light alloy, are peripherally supported from the end ones.
  • the said other discs may be relatively-thin, plain discs with slightly enlarged hollow hubs providing a passage for cooling air.
  • each of the light alloy discs is provided, at one side, with a short axial flange within which spigots the axial extremity of the aforesaid axially-extending portion of the adjacent disc, and radially outwardly of this flange is the radiallocating peripheral groove for the roots of a blade row.
  • such groove may be of T-section, fir-tree section, or preferably of dovetail section.
  • the steel disc at one end may have a spigotal engagement with an independent, axially-extending n'ng (preferably of light alloy) providing the adjacent shroud and bolted to the steel disc jointly to provide therewith the radial-locating peripheral groove for the roots of the blade row at that end.
  • n'ng preferably of light alloy
  • All the blades may be inexpensively formed of a plastic moulded to shape and incorporating a filler of asbestos or other heat-resisting material.
  • the light-alloy discs are die cast, to obviate the necessity for machining; but when the discsare not die cast the machining operations are easy turning ones, which allows of their production at low cost.
  • each set of retaining bolts lie on a pitch circle which is coincident with the cylindrical surface of the, spigotal engagement, being as near the blade roots as is conveniently possible.
  • Figure 1 is a diagrammatic view of a gas turbine engine 2,738,126 Patented Mar. 13, 1956 including an air intake A, an axial-flow compressor B,
  • annular combustion chamber C (although this latter could be a ring of separate combustion chamber units), an axial-flow turbine D, and a jet pipe E;
  • Figure 2 is an axial section of an axial-flow compressor constructed in accordance with the invention, parts being omitted for the sake of clearness;
  • Figure 3 is a fragmentary section similar to Figure 2 but to a larger scale and showing rotor blade roots of a different form;
  • Figure 4 is a view similar to Figure 3 but showing a modified construction
  • Figures Sand 6 are sections, respectively, on the lines 5-5 and 6-6 of Figure 4;
  • Figure 7 shows a modified (as compared with Figure 5) form of blade for mounting in the compressor.
  • Figure 8 is an exploded, fragmentary perspective view showing the relationship between one of the fixing bolts and one of the spigoting parts.
  • the compressor of which an intermediate length has been omitted, has rows of radial stator blades 11, 11 fast at their radially-outer ends with a stator casing 12, and, at the upstream and downstream ends, respectively, the stator has diaphragms 13, 14 which support bearing 15, 16 for aligned shaft portions 17, 18
  • the latter comprises steel end discs 19, Zli, of which central hubs provide the shaft portions 17 and 18, and
  • Each of the discs 21, which are of light alloy, is formed with an axially-extending peripheral portion 22 having a flange 23 spigotally engaged within an oppositely, axiallydirected annular flange 24 of the discadjacent its righthand side in Figure 2, the portion 22 of the extreme right-hand disc 21 (not shown) having a similar engagement with a similar flange 24a of the right-hand end disc 20.
  • An independent axially-extending ring 22a has flanges 23a and 23b similarly spigotally engaging within the flange 24 of the left-hand disc 21, and a flange 24b of the left-hand end disc 19, respectively.
  • Each disc 21 has a central hole 50, for cooling air.
  • the discs 19, 20 and 21, and the portions 22 and ring 22a have grooves 31 to receive the roots 32 of associated rows of rotor blades 33, and the portions 22 and ring 22a act as shrouds between the rows. It can be arranged, according to the profile of the rotor blade roots, for there to be axial clearance between the bottoms of the grooves and the roots (as shown in Figure 2) and for flanges 34 to grip necks of the roots when the nuts 30 are tightened, or for the grooves and roots to have a wedging engagement as shown in Figure 3 or 4.
  • the compressor can have air-inlet guide vanes 35, and air-outlet guide vanes 36, these vanes being fast with the stator and the vanes 36 directing the compressed air into passages 37, 38, 39 leading to a combustion chamber.
  • the embodiment shown in Figures 4 to 6 differs from that of Figure 2 mainly in the way the blades, which are preferably of molded plastic, are supported.
  • the blades 33 are fast with platforms 40 which are chamfered at the up-stream and down-stream edges to have a dovetail engagement with the grooves 31a.
  • the intermediate edges 41 of the platforms are also chamfered and are located by reversely bevelled edges of fillets &2, the up-stream and down-stream edges of the fillets also being bevelled to have a dovetail engagement with the grooves 31a.
  • the platforms and, of course, the fillets
  • the fillets are parallelogram-like in plan.
  • T he blade shown in Figure 7 has a rectangular platform 40a of which the up-stream and down-stream edges are bevelled, like those of the platform 40 of Figure 5, to have a dovetail engagement with the grooves 3111, the intermediate edges 41a in this case lying in planes which are radial of the rotor axis so as to pack closely together when the blades of a row are assembled.
  • the portions 22 and the ring 2201 their radially inner edges can be relieved, as indicated at 44 in Figure 6, intermediate the bolting positions where bosses 43 are left to accommodate the bolts 25, 25a.
  • the platforms 4i and 40a can be hollowed on the underside as shown in Figure 4.
  • a demountable axial-flow bladed compressor rotor comprising opposite end discs fast with respective outwardly-extending coaxial shaft portions, a plurality of concentric intermediate thin discs with axially-extending peripheral portions at their corresponding one sides, each of said axially-extending portions having at its extremity a radially-inwardly directed flange which is formed on its outer axial side for spigotal engagement with the adjacent disc, an axially-extending ring between said end disc and the extreme intermediate disc whose axially-extending portion is remote from the adjacent end disc, said ring being provided at its ends with radially-inwardly directed flanges which are formed on their outer axial sides for spigotal engagement respectively with the adjacent end and intermediate discs, said ring and axially-extending peripheral portions constituting shrouds and supporting said intermediate discs from said end discs in mutually spaced relation whereby to form a light hollow structure which is internally reinforced against centrifugal loads by said discs and which is supported from said shaft portions, each
  • a demountable axial-flow bladed compressor rotor comprising opposite end discs fast with respective outwardly-extending coaxial shaft portions, a plurality of concentric intermediate thin discs with axially-extending peripheral portions at their corresponding one sides, each of said axially-extending portions having at its extremity a radially-inwardly directed flange formed on its outer axial side with an annular step, each of said intermediate discs on the side opposite said axially-extending portion formed with an annular ridge, the adjacent steps and ridges forming a spigot for inter-engaging adjacent discs and axially-extending portions, said axially-extending portions forming shrouds, an axially-extending ring between the extreme intermediate disc whose axiallyextending portion is remote from the adjacent end disc and said end disc, said ring having at each end a radiallyinwardly directed flange, said ring flanges each having an annular step, the said end disc having an annular ridge for spigotal engagement with the adjacent annul

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US256475A 1950-12-08 1951-11-15 Construction of compressor rotors Expired - Lifetime US2738126A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB316506X 1950-12-08

Publications (1)

Publication Number Publication Date
US2738126A true US2738126A (en) 1956-03-13

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US256475A Expired - Lifetime US2738126A (en) 1950-12-08 1951-11-15 Construction of compressor rotors

Country Status (6)

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US (1) US2738126A (d)
BE (1) BE507205A (d)
CH (1) CH316506A (d)
DE (1) DE967778C (d)
FR (1) FR1056070A (d)
GB (1) GB695221A (d)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795393A (en) * 1952-07-10 1957-06-11 Havilland Engine Co Ltd Rotors of multi-stage axial flow compressors or turbines
DE1067971B (d) * 1955-10-18 1959-10-29
DE1095453B (de) * 1955-07-18 1960-12-22 Rolls Royce Mehrstufige Axialstroemungsmaschine
US3345035A (en) * 1965-04-30 1967-10-03 Gen Motors Corp Turbine wheel
US4688992A (en) * 1985-01-25 1987-08-25 General Electric Company Blade platform
EP1319842A1 (fr) * 2001-12-17 2003-06-18 Techspace Aero S.A. Rotor ou élément rotorique pour turbocompresseur
US20030143078A1 (en) * 2001-12-17 2003-07-31 Dante Benedetto Rotor or rotor element for a turbocompressor
EP1462664A2 (en) 2003-03-28 2004-09-29 General Electric Company Methods and apparatus for joining gas turbine parts together
US20050238423A1 (en) * 2004-04-23 2005-10-27 Snecma Moteurs Fastener system for fastening together parts using pins having collars
CN102099147A (zh) * 2008-07-18 2011-06-15 斯奈克玛 涡轮机轮盘的修复或再加工方法以及经修复或再加工的涡轮机轮盘
US20110206504A1 (en) * 2008-08-26 2011-08-25 Snecma Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly
EP2236757A3 (en) * 2009-03-17 2013-10-23 United Technologies Corporation Split rotor disk assembly for a gas turbine engine
US20160169246A1 (en) * 2013-07-12 2016-06-16 United Technologies Corporation Plastic variable inlet guide vane

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884186A (en) * 1954-04-23 1959-04-28 Stalker Corp Rotor construction for axial flow compressors
US2804323A (en) * 1954-08-19 1957-08-27 Rolls Royce Axial-flow compressors and turbines
DE1062881B (de) * 1956-08-24 1959-08-06 Krantz H Fa Axialventilator mit bei Stillstand im Nabenkranz auf verschiedene Anstellwinkel einstellbaren Laufschaufeln
DE1080255B (de) * 1957-01-17 1960-04-21 Andreas Harold Andersen Axialventilator
FR1245518A (fr) * 1957-04-19 1960-11-10 Perfectionnements apportés aux turbines à fluide gazeux chaud
FR2607866B1 (fr) * 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
US5378110A (en) * 1992-09-14 1995-01-03 United Technologies Corporation Composite compressor rotor with removable airfoils
GB2303188B (en) * 1995-07-13 1999-04-28 Bmw Rolls Royce Gmbh An assembly of two turbine rotor discs
US12247516B2 (en) 2022-09-29 2025-03-11 General Electric Company Counter-rotating gas turbine engines including turbine sections with separable torque frames

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US768597A (en) * 1902-08-21 1904-08-30 Gen Electric Turbine-bucket.
US980732A (en) * 1910-07-09 1911-01-03 Gen Electric Bucket structure for turbines.
US1118361A (en) * 1914-06-19 1914-11-24 Gen Electric Wheel for elastic-fluid turbines.
GB394001A (en) * 1931-12-18 1933-06-19 Parsons C A & Co Ltd Improvements in and relating to built-up rotors, suitable for steam turbines
DE729493C (de) * 1941-01-07 1942-12-17 Siemens Ag Aus axial miteinander verschraubten Drehkoerpern zusammengesetzter Laeufer fuer Kreiselmaschinen, insbesondere Dampf- oder Gasturbinen
GB578191A (en) * 1941-11-21 1946-06-19 Frank Bernard Halford Improvements in or relating to turbines
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
GB642287A (en) * 1948-07-01 1950-08-30 English Electric Co Ltd Improvements in and relating to the connection of spigotted components of multi-stage compressor rotors

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE840880C (de) * 1941-09-08 1952-06-09 Daimler Benz Ag Laufrad fuer Axialturbomaschinen, insbesondere fuer Axialverdichter
FR895583A (fr) * 1942-05-21 1945-01-29 Roue motrice ou rotor pour turbines à gaz refroidies
GB579425A (en) * 1943-10-06 1946-08-02 Frank Robert Bell Improvements in blade drums for axial-flow compressors and turbines
US2452782A (en) * 1945-01-16 1948-11-02 Power Jets Res & Dev Ltd Construction of rotors for compressors and like machines
FR1012335A (fr) * 1949-07-13 1952-07-08 Hispano Suiza Sa Perfectionnements apportés aux engins, notamment aux compresseurs axiaux, à rotor équipé de plusieurs aubages disposés en tandem

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US768597A (en) * 1902-08-21 1904-08-30 Gen Electric Turbine-bucket.
US980732A (en) * 1910-07-09 1911-01-03 Gen Electric Bucket structure for turbines.
US1118361A (en) * 1914-06-19 1914-11-24 Gen Electric Wheel for elastic-fluid turbines.
GB394001A (en) * 1931-12-18 1933-06-19 Parsons C A & Co Ltd Improvements in and relating to built-up rotors, suitable for steam turbines
DE729493C (de) * 1941-01-07 1942-12-17 Siemens Ag Aus axial miteinander verschraubten Drehkoerpern zusammengesetzter Laeufer fuer Kreiselmaschinen, insbesondere Dampf- oder Gasturbinen
GB578191A (en) * 1941-11-21 1946-06-19 Frank Bernard Halford Improvements in or relating to turbines
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
GB642287A (en) * 1948-07-01 1950-08-30 English Electric Co Ltd Improvements in and relating to the connection of spigotted components of multi-stage compressor rotors

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795393A (en) * 1952-07-10 1957-06-11 Havilland Engine Co Ltd Rotors of multi-stage axial flow compressors or turbines
DE1095453B (de) * 1955-07-18 1960-12-22 Rolls Royce Mehrstufige Axialstroemungsmaschine
DE1067971B (d) * 1955-10-18 1959-10-29
US3345035A (en) * 1965-04-30 1967-10-03 Gen Motors Corp Turbine wheel
US4688992A (en) * 1985-01-25 1987-08-25 General Electric Company Blade platform
EP1319842A1 (fr) * 2001-12-17 2003-06-18 Techspace Aero S.A. Rotor ou élément rotorique pour turbocompresseur
US20030143078A1 (en) * 2001-12-17 2003-07-31 Dante Benedetto Rotor or rotor element for a turbocompressor
EP1462664A3 (en) * 2003-03-28 2007-03-28 General Electric Company Methods and apparatus for joining gas turbine parts together
EP1462664A2 (en) 2003-03-28 2004-09-29 General Electric Company Methods and apparatus for joining gas turbine parts together
US20050238423A1 (en) * 2004-04-23 2005-10-27 Snecma Moteurs Fastener system for fastening together parts using pins having collars
US7766574B2 (en) * 2004-04-23 2010-08-03 Snecma Fastener system for fastening together parts using pins having collars
CN102099147A (zh) * 2008-07-18 2011-06-15 斯奈克玛 涡轮机轮盘的修复或再加工方法以及经修复或再加工的涡轮机轮盘
US20110176921A1 (en) * 2008-07-18 2011-07-21 Snecma Method of repairing or reworking a turbomachine disk and repaired or reworked turbomachine disk
US8864472B2 (en) * 2008-07-18 2014-10-21 Snecma Method of repairing or reworking a turbomachine disk and repaired or reworked turbomachine disk
US20110206504A1 (en) * 2008-08-26 2011-08-25 Snecma Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly
US8864458B2 (en) * 2008-08-26 2014-10-21 Snecma Fixed vane assembly for a turbine engine having a reduced weight, and turbine engine comprising at least one such fixed vane assembly
EP2236757A3 (en) * 2009-03-17 2013-10-23 United Technologies Corporation Split rotor disk assembly for a gas turbine engine
US20160169246A1 (en) * 2013-07-12 2016-06-16 United Technologies Corporation Plastic variable inlet guide vane
US10233941B2 (en) * 2013-07-12 2019-03-19 United Technologies Corporation Plastic variable inlet guide vane

Also Published As

Publication number Publication date
DE967778C (de) 1958-01-16
CH316506A (fr) 1956-10-15
BE507205A (d)
GB695221A (en) 1953-08-05
FR1056070A (fr) 1954-02-24

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