US2931625A - Compressor rotor - Google Patents

Compressor rotor Download PDF

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Publication number
US2931625A
US2931625A US628682A US62868256A US2931625A US 2931625 A US2931625 A US 2931625A US 628682 A US628682 A US 628682A US 62868256 A US62868256 A US 62868256A US 2931625 A US2931625 A US 2931625A
Authority
US
United States
Prior art keywords
slot
blades
blade
rotor
blade holding
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
US628682A
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English (en)
Inventor
Lechthaler Louis Harold
Feinberg Seymour Jacob
Whited Henry Le Baron
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US628682A priority Critical patent/US2931625A/en
Priority to GB36997/57A priority patent/GB827264A/en
Priority to FR1192330D priority patent/FR1192330A/fr
Priority to DEG23543A priority patent/DE1134472B/de
Application granted granted Critical
Publication of US2931625A publication Critical patent/US2931625A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/30—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
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys

Definitions

  • the present invention relates to rotors for compressors or the like and more particularly to rotors for axial flow type compressors used in small turbo engines for aircraft. More specifically, the invention relates to such a rotor in which the compressor blades are individually attachable to and detachable from the rotor.
  • An object of the present invention is to provide such a rotor in which the time, skill and labor involved in attaching and detaching the individual blades is reduced to a minimum, in which the blades can be attached and detached without the necessity of utilizing complicated accessory too'ls such as turn tables,V means for measuring run outs and parallelism, etc., in which the conventional and complicated blade coupling and fastening elements such as discs, top rings, splines, anges, a plurality of bolts, etc., are eliminated and which is simple in construction and has a minimum number of separate parts.
  • a further object is to provide such a rotor in which the compressor blades can beindividually attached and detached without the necessity of disassembling the rotor from its installation.
  • a still further object is to provide such a rotor'in which the blades can be attached and detached without removing any parts other than the blades, in which the only parts which must be handled other than the blades in disassembling and assembling the blades comprises a simple, inexpensive locking member for each row of blades, such member being easily accessible while the rotor is installed, and in which the only manipulation other than movement of the blades themselves required to assemble and disassemble the blades of each row is a simple turning movement of the single locking member.
  • Another further object is to provide such a rotor which is simple and inexpensive to assemble, disassemble, service and manufacture but yet which isrugged and'durable and requires a minimum of maintenance. Because of its simplicity in construction and the small number of parts, it is more stable so that there is less likelihood of unbalance, and hence less correction is required, than in conventional built up rotor designs. Its simplicity and small number of parts also eliminates a large factor in the stack up of tolerances usually present in conventional built up blade arragements so that smaller radial and axial clearances are possible.
  • Another still further object is to provide such a rotor in which the locking mechanism for locking the blades in attached position is locked against accidental removal when the blades are assembled and is urged into locking position by the centrifugal force of the rotating rotor.
  • Fig. l is a cross section in elevation of a portion of a rotor embodying the present invention'.
  • Fig. 2 is a plan View of a portion of the roto-r of Fig. l.
  • Fig. 3 is an enlarged view of the locking mechanism of Fig. 2.
  • Fig. 4 is a view taken along the line 4--4 of Fig. 2.
  • Fig. 5 is a plan view showing the entry slot.
  • Fig. 6 is a vieu/.taken along the line 6-6 of Fig. 2 with the portion of the blade holding member between the line 6--6 and the blade holding slot being cut away and sho-wing only two adjacent blades.
  • Fig. 7 is an enlarged view of one of the blades of Fig. l.A
  • Fig. 8 is a view showing one of two locking blades of Fig. 2, and showing the shape of the entry slot.
  • 1 is a generally cylindrically shaped, hollow spool or drum onev which extend therearound and which ⁇ also extend inwardly intointernal annular ribs 9.
  • the periphery of spool 1 has a plurality of blade hold
  • each slot 10 extending into the thickened portion 8 and lying in a plane which is perpendicular to the longitudinal center line of the spool.
  • Each slot 10 (see Figs. 4 and 6) comprises a lower, wider portion 11 which extends upwardly into a narrow neck 13, which diverges outwardly at 15 as shown.
  • Each slot 10 slidably receives the dove tail shaped roots 14 of a plurality of Vblades 12, 12a, and 12b.
  • Each root 14 has a widened lower portion 11a which is received by portion 11 of the slot, a narrow neck portion 13a received by the narerow neck portion 13 of the slot, and an upwardly diverg-4 ing portion 15a, which is received by the diverging portion 15 of the slot.
  • the upwardly flared portion 15a of each root extends upwardly into a at, substantially rectangular shaped platform 16 or 16a which in turn extends upwardly into a blade portion 18.
  • Some of the end walls 20 of platforms 16 are beveled and some are not dependingV on the position which the blade occupies on the member 1.
  • the circumferential width b of root 14 (see Figs. 2 and 6) is about 50% of the circumferential width of end wall 20 of the platforms.
  • the top ared out portions 15 of the slot 10 are shaped or counter sunk to receive the platforms 16 so that the top of the platforms are flush with the periphery of the drum.
  • the adjacent side edges 22 of the platforms 16 or 16a abut each other when all the blades are assembled as shown so that sliding movement of each blade in the slot with relation to the other blade is prevented and sliding movement of one blade in the slot causes all the blades to be moved as a unit.
  • the roots 14 are inserted into blade holding slot 10 by means of an entry slot 24, see Figure 5, which is sufficiently wider than the blade holding slot 10 and the wide* portions 13a of the roots to permit them to'be inserted of the slot 10.
  • top flared out parts 15 of the end portions of slot 10 adjacent ⁇ j entry slot 24 extend laterally in one direction further than the top flared out part 15 of the rest of the slot 10 to form a rabbet or recess 28 in member 1.
  • One end 27 of the rabbet is curvilinear in shape and the other endA forms a shoulder 32.
  • the platforms 16a of these two blades 12a and 12b are greater in axial width than the platforms 16 of the other blades and extend laterally at 30a beyondthe bases of their blade portions 18 into the rabbet 28. As shown in Figs. 4 and 8 the rabbet is contoured to snugly receive these laterally extending portions 30a so that the surfaces of the platforms 16a are llush with the periphery of spool 1 just like the top surfaces of the other platforms 16. Except for these laterally extending portions 30a of platforms 16a, blades 12a and 12b are similar to the other blades 12. v
  • the laterally extending portions 30a of platforms 16a are locked between the shoulder 32 of rabbet 28, against which the side edge 30 of widened portion 30a of blade 12a abuts, and a narrow shankV portion 34 of set screw 35 which engages the edge 36 of portion 30a of blade 12b and which protrudes from the threaded aperture 40 in spool 1 into the rabbet.
  • the threaded aperture 40 is deep enough so that the screw 35 can be fully retracted into it, including the'shank portion 34, whereby the portions 30a are no longer locked against movement( in rabbet 2 8 and the blades can be removed and inserted in the slot 10 as hereinafter described.
  • the edge 36 of blade 12b overlies a portion of the aperture 40 and thereby engages the shoulder 44 formed between shank 34 and threads 38 of screw 35 when the screw is moved out of its aperture to its locking position shown in Fig. 6, whereby accidental removal of the screw from the aperture is prevented.
  • the rabbet 28 is long enough so that when the scre 35 is fully retracted into aperture 4t) the portions 30a can be moved into the rabbet a Vsufficient distance toward end 27 to permit the root of blade 12a to clear the end 26a of slot 10 and move entirely into entry slot 24, whereafter blade 12a can be lifted out of the entry slot.' Subsequently, the rest of the blades can be removed by sliding their roots into entry slot 24 and lifting them out of the entry slot. Movement of the portions 30a in rabbet 28 to move the root of 12a into entry slot 24 causes the entire row of blades to slide as a unit in slots 10 and 24 and thereby causes the root of blade 12b to move further into the end 26 of slot 10.
  • the blades are assembled by individually inserting the roots of all the blades 12 into the slot 10 via the entry slot 24 while the screw 35 is retracted into the aperture 4Q, Thereafter, the root of blade 12b is inserted into ⁇ the end 26 of the slot 10 via entry slot 24 and moved into the slot until the edge 36 of portion 30a thereof abuts against end27-of rabbet 28.
  • the rabbet 2S is long enough so that the blade 12b can be moved into slot and consequently urges shoulder 44 into engagement with the underside of that part of portion 30aV of bladc 12b which overlies the aperture.
  • the compressor blades rotate between stator vanes 18a xedly attached to the stator casing.
  • the rotor of the present invention is made up only of the rotor drum,'a screw for each slot and the blades.
  • the only tool necessary to attach and detach the blades is an Allen wrench or screw driver, which can be used to screw and unscrew the screw into and out of aperture 40.
  • the blades can be attached and detached without disassembliag the rotor from its installation and without the removal of any part from the rotor other than blades. To replace a defective blade it is necessary only to unlock the row in which the blade is located. The defective blade ca n be replaced while the rotor is installed and without handling any of the blades other than those in the row in which the defective blade is located.
  • a rotor for axial ow compressors or the like comprising a generally cylindrical shaped blade holding member having at least one dove-tail shaped blade holding slot in the periphery thereof, a plurality of blades, each of said blades formed with a dove-tail root slidably received by said blade holding slot, the blade holding slot and root being vsuch that the root is locked against movement with respect to said blade holding slot other than sliding movement longitudinally along the blade holding slot, said member having a rabbet recess formed in a longitudinal edge of said slot, an entry slot formed in said blade holding slot along said rabbet recess for insertion and removal of said roots into said blade holding slot, at least one of said blades having an extension extending into said rabbet and slidable into abutment upon an edge thereof to l :event sliding movement of said roots inV one direction along said blade holding slot, and locking means extending from said blade holding member for locking said extension against movement in a second direction longitudinally along said slot to prevent movement of said
  • a rotor for an axial flow compressor comprising a blade holding member having at least one dove-tail shaped blade holding slot extending around the periphery thereof, a plurality of blades having dove-tail root portions thereon slidably received in said slot, the dove-tail shape of said slot yand said root portions being such as to restrain said root portions against radial movement relative to*4 said blade holding member, an entry slot extending intorsaid blade holding slot to permit insertion and removal of'saidfblade roots into and from said blade holding slot, a recess in said blade holding member positioned laterally adjacent said entry slot, portions of two of said blades extending laterally into said recess, an aperture in said recess, and a locking member having a narrow head portion and a base portion mounted in said aperture and extending radially therefrom, said locking member being adjustable radially inward to permit insertion and removal of said blade roots through said entry slot and adjustable radially outward to bring the shoulder between said narrow head portion and said base portion into
  • a bladed rotor for accommodating axial uid ow therethrough comprising a blade holding member, a dovetail shaped blade holding slot extending around the pe riphery of said blade holding member, a plurality of blades each having a dove-tail root portion thereon, the root portion of each of said blades being slidably received in said slot, the dove-tail shapeof said slot and said blade roots being such that the roots are restrained against radial movement with respect to said blade holding member, an entry slot extending into said blade holding slot to permit insertion and removal of said blade roots into and from said blade holding slot, a laterally extending recess in said blade holding member adjacentsaid entry slot, at least one of said blades having a laterally extending portion thereon extending into said recess when said blades are assembled in said blade holding slot, and a locking member mounted in said recess and engaging the portion of said blade extending into said recess to restrain peripheral movement of said blades in one direction.
  • a rotor for axial ilow compressors or the like comprising a blade holding member having at least one dovetailYV shaped blade holding slot extending around the periphery thereof, a plurality of blades each having a dove-tail root, each of said roots slidably received by said blade holding slot, the shape of said blade holding slot and said roots being such that said roots are locked against movement with respect to said slot other than sliding movement longitudinally in said slot, an entry slot extending into said blade holding slot for inserting and removing said roots into and from said blade hold- ⁇ ing slot, a first portion of the root of at least one of said blades extending into said entry slot and a second portion thereof extending into said blade holding slot when said rotor is in an assembled state, and means for locking said blades against removalv from and sliding movement in said blade holdingslot, said last mentioned means comprising a locking member extending from said blade holding member into engagement with iirst portion of said oneof said blades to prevent movement of said second portion ther-of into

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US628682A 1956-12-17 1956-12-17 Compressor rotor Expired - Lifetime US2931625A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US628682A US2931625A (en) 1956-12-17 1956-12-17 Compressor rotor
GB36997/57A GB827264A (en) 1956-12-17 1957-11-27 Improvements in compressor rotor
FR1192330D FR1192330A (fr) 1956-12-17 1957-12-06 Rotor de compresseur du type à écoulement axial
DEG23543A DE1134472B (de) 1956-12-17 1957-12-16 Laufrad fuer Axialstroemungskompressoren

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US628682A US2931625A (en) 1956-12-17 1956-12-17 Compressor rotor

Publications (1)

Publication Number Publication Date
US2931625A true US2931625A (en) 1960-04-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
US628682A Expired - Lifetime US2931625A (en) 1956-12-17 1956-12-17 Compressor rotor

Country Status (4)

Country Link
US (1) US2931625A (fr)
DE (1) DE1134472B (fr)
FR (1) FR1192330A (fr)
GB (1) GB827264A (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053504A (en) * 1960-01-18 1962-09-11 Rolls Royce Method of assembling a bladed member
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
US20060275111A1 (en) * 2005-06-06 2006-12-07 General Electric Company Forward tilted turbine nozzle
US20060272314A1 (en) * 2005-06-06 2006-12-07 General Electric Company Integrated counterrotating turbofan
US20060288686A1 (en) * 2005-06-06 2006-12-28 General Electric Company Counterrotating turbofan engine
US20130323064A1 (en) * 2012-05-31 2013-12-05 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US20140182293A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Compressor Rotor for Gas Turbine Engine With Deep Blade Groove
US12049833B1 (en) 2023-05-26 2024-07-30 General Electric Company Rotor disks with disk post inserts and methods of assembling the same

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
US3263962A (en) * 1965-04-22 1966-08-02 Gen Motors Corp Rotor blade lock
US3742706A (en) * 1971-12-20 1973-07-03 Gen Electric Dual flow cooled turbine arrangement for gas turbine engines
US3981623A (en) * 1975-05-02 1976-09-21 General Motors Corporation Turbomachine rotor stage
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
GB2119026B (en) * 1981-03-25 1984-06-20 Rolls Royce Aerofoil blade mounting
GB2097480B (en) * 1981-04-29 1984-06-06 Rolls Royce Rotor blade fixing in circumferential slot
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
CN102979763B (zh) * 2012-12-29 2015-09-16 成都成发科能动力工程有限公司 轴流式压缩机转子动叶片安装结构及动叶片安装方式

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US672838A (en) * 1900-03-01 1901-04-23 Westinghouse Machine Co Fluid-pressure turbine.
US1010630A (en) * 1908-05-26 1911-12-05 Colonial Trust Co Blade-holding means for turbines.
US1687891A (en) * 1924-09-08 1928-10-16 Westinghouse Electric & Mfg Co Blade fastening
US1705585A (en) * 1924-09-08 1929-03-19 Westinghouse Electric & Mfg Co Turbine-blade fastening
DE560951C (de) * 1931-09-01 1932-10-08 Oerlikon Maschf Schaufelschloss fuer Turbinenbeschaufelung
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus
US2393447A (en) * 1944-05-20 1946-01-22 Allis Chalmers Mfg Co Turbine blade locking apparatus
US2434935A (en) * 1946-02-08 1948-01-27 Westinghouse Electric Corp Turbine apparatus
US2619318A (en) * 1946-06-07 1952-11-25 Sulzer Ag Turbomachine rotor
US2667327A (en) * 1950-06-14 1954-01-26 Westinghouse Electric Corp Rotor construction

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH240276A (de) * 1942-08-13 1945-12-15 Sulzer Ag Axiale Turbomaschine und Verfahren zu deren Herstellung.
BE490366A (fr) * 1948-09-17
DE803181C (de) * 1948-10-02 1951-03-01 Maschf Augsburg Nuernberg Ag Schaufelschloss fuer axiale Kreiselradmaschinen

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US672838A (en) * 1900-03-01 1901-04-23 Westinghouse Machine Co Fluid-pressure turbine.
US1010630A (en) * 1908-05-26 1911-12-05 Colonial Trust Co Blade-holding means for turbines.
US1687891A (en) * 1924-09-08 1928-10-16 Westinghouse Electric & Mfg Co Blade fastening
US1705585A (en) * 1924-09-08 1929-03-19 Westinghouse Electric & Mfg Co Turbine-blade fastening
DE560951C (de) * 1931-09-01 1932-10-08 Oerlikon Maschf Schaufelschloss fuer Turbinenbeschaufelung
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus
US2393447A (en) * 1944-05-20 1946-01-22 Allis Chalmers Mfg Co Turbine blade locking apparatus
US2434935A (en) * 1946-02-08 1948-01-27 Westinghouse Electric Corp Turbine apparatus
US2619318A (en) * 1946-06-07 1952-11-25 Sulzer Ag Turbomachine rotor
US2667327A (en) * 1950-06-14 1954-01-26 Westinghouse Electric Corp Rotor construction

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053504A (en) * 1960-01-18 1962-09-11 Rolls Royce Method of assembling a bladed member
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
US7510371B2 (en) 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
US20060272314A1 (en) * 2005-06-06 2006-12-07 General Electric Company Integrated counterrotating turbofan
US20060288686A1 (en) * 2005-06-06 2006-12-28 General Electric Company Counterrotating turbofan engine
US20060275111A1 (en) * 2005-06-06 2006-12-07 General Electric Company Forward tilted turbine nozzle
US7513102B2 (en) 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7594388B2 (en) 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
US20130323064A1 (en) * 2012-05-31 2013-12-05 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US9097131B2 (en) * 2012-05-31 2015-08-04 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US20140182293A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Compressor Rotor for Gas Turbine Engine With Deep Blade Groove
US12049833B1 (en) 2023-05-26 2024-07-30 General Electric Company Rotor disks with disk post inserts and methods of assembling the same

Also Published As

Publication number Publication date
GB827264A (en) 1960-02-03
FR1192330A (fr) 1959-10-26
DE1134472B (de) 1962-08-09

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