US3778191A - Blade mounting - Google Patents

Blade mounting Download PDF

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Publication number
US3778191A
US3778191A US00108350A US3778191DA US3778191A US 3778191 A US3778191 A US 3778191A US 00108350 A US00108350 A US 00108350A US 3778191D A US3778191D A US 3778191DA US 3778191 A US3778191 A US 3778191A
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United States
Prior art keywords
blade
base plate
arrangement according
fastening arrangement
portions
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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
US00108350A
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English (en)
Inventor
H Brockmann
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Daimler Benz AG
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Daimler Benz AG
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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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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

Definitions

  • ABSTRACT A blade fastening for the blades of compressors and/or [30] Foreign Applicatio Pri rity D818 turbines, especially for blades retained in dove-tail Jan. 21, 1970 Germany P 20 02 469.5 ang n al gr ves pr vided along the outer diameter of the rotor disks; the webs of the tangential grooves [52 ⁇ 11.8. CI. 416/215 cover the h mmer-head-like bases of the blades sub- [51] Int. Cl.
  • This type of blade-rotor connection permits a very simpletype of construction; for example, the rotor may be manufactured of a welded construction realizable in a very simple manner and the rotor blades are inserted into the rotor following the assembly of the rotor.
  • This groove shape is particularly advantageous for rotors of fiber-reinforced plastic materials such as synthetic resinous materials of any conventional type, because the fiber-flow is not interrupted thereby. It is known to construct rotor blades with hammer-head shaped bases and to introduce the same into the tangential groove of the rotating disk.
  • apertures disturb theflow of the lines of force at the outer circumference of the rotor, which in particular, in case of turbines with very high rotational speeds and larger dimensions, leads to large stresses in the rotor as a result of the occurring centrifugal forces, which can be absorbed only by additional reinforcements and greater structural weight.
  • the apertures for the fastening sheet metal member represent a further interruption for the flow of the lines of force.
  • the present invention is concerned with the task to avoid these disadvantages and to provide a blade fastening or blade mounting, in which the blades are adapted to be inserted into the rotor in a simple manner and a displacement or movementof the blades on the rotor isprevented. Furthermore, for the installation of the blades, noapertures extending transversely over the disk width in the tangential groove at the outer diameter of the rotor disk have to be provided which interrupt the force flow.
  • the underlying problems are solved according to the present invention in that the webs of the tangential priate if the hammer-head-shaped bases are arranged obliquely to the rotor disk axis and are adapted to be so inserted into the tangential groove by a rotation that they almost completely fill the groove cross section.
  • the base plates of the blades may have a differing width in the circumferential direction and the base plates, especially of the blades inserted last, may be shortened on one side or on both sides thereof in relation to the blades.
  • a residual gap remains between the blades inserted last, into which a further blade cannot be inserted by reason of the necessary rotation. Since the blades in the assembled condition must have a constant spacing from one another, and since this constant spacing is not attained by the shortened base plates of the blades inserted last, it is very appropriate if the gaps formed between the shortened base plates are filledby filler elements.
  • the filler elements may be advantageously subdivided centrally thereof in a radial direction and in the assembled condition may exhibit the outer contour of the blade base with a base plate and may be retained underneath the webs of the grooves.
  • the gap forming between the base plates is filled by two filler elements which in the pushed-together condition bridge the gap between the base plates.
  • one or several transmitting elements may be inserted into the arcuately shaped apertures disposed opposite the webs of the tangential groove.
  • These transmitting elements may be provided advantageously with rounded-off outer edges that are adapted essentially to the base shape of the blades and are retained in the apertures by locking or wedging.
  • the transmitting elements may appropriately terminate underneath the base plates of the blades and may be covered in the assembled and installed condition by the blade plates pushed against one another sothat they are not visible with a completely assembled rotor.
  • a locking element may be inserted into the remaining residual gap which is arranged in the assembled condition transversely to the base plate edges by a rotation and engages from below the adjacent blade base plates.
  • the locking means is constituted by a curved double sheet metal element or plate and is provided at its upper edge with two tab or lug-shaped tongue portions that are bent in between the adjacent base plates of the blades in the installed and assembled condition of the locking means and fill out the residual gap in its width in that they adapt themselves to the gap shape between the two base plates of the blades. The locking element thus cannot rotate back and furthermore the two adjacent blades can no longer move toward one another.
  • the length of the plate-shaped tongue portions is so selected that in their length they do not fill out the entire residual gap so that, if necessary, they can be readily bent open again with a hookshaped tool during the disassembly and the lock can be disassembled and removed again by rotation.
  • the lock can be economically manufactured in its starting shape from sheet metal, for example, advantageously by spray-etching. After it has been brought into the shape necessary for the installation by appropriate bending together, the two surfaces with the exception of the tabs or lugs may be caused to adhere at one another by any conventional appropriate process.
  • Another object of the present invention resides in a blade fastening which eliminates the need for relatively large apertures in the rotor while minimizing large stresses in the rotor which may be caused by centrifugal forces.
  • a further object of the present invention resides in a blade fastening for rotors of compressors or turbines made of plastic material which does not disturb the flow of the lines of force along the outer circumference of the rotor.
  • Still a further object of the present invention resides in a blade fastening for the blades of a rotor of compressors or turbines which permits an easy assembly of the blades in the rotor yet precludes any movement of the blades along the rotor circumference.
  • a further object of the present invention resides in a blade fastening for rotor blades of compressors and/or turbines which permits the use of relatively simple elements, easy to manufacture, and assures a completely safe and secure mounting of the blades in the rotor without danger of any displacements of the blades.
  • FIG. 1 is a schematic longitudinal cross-sectional view of one-half of a welded rotor with blades inserted into the rotor disks;
  • FIG. 2 is a partial cross-sectional view, on an enlarged scale, through a rotor disk with an inserted blade;
  • FIG. 3 is a plan view on the rotor disk with inserted blades and with an inserted transmitting element
  • FIG. 4 is a cross-sectional view, on an enlarged scale, through the rotor disk with an inserted blade and with an inserted transmitting element;
  • FIG. 5 is a plan view on the rotor disk, with inserted filler elements in the upper part thereof and with filler elements not yet assembled in the lower part thereof;
  • FIG. 6 is a partial cross-sectional view, on an enlarged scale, through the rotor disk with inserted filler elements
  • FIG. 7 is an elevational view of a lock in prefinished condition
  • FIG. 8 is a plan view on the rotor disk with inserted filler elements and with an inserted lock
  • FIG. 9 is a partial cross-sectional view, on an enlarged scale, through the rotor disk with inserted lock, taken in the direction of arrow IX-IX of FIG. 8.
  • FIG. 1 a welded compressor rotor is schematically indicated in this figure in longitudinal cross section.
  • Five rotor disks 2, 2a are provided which have a tangential groove 3 at the outer diameter thereof, into which are inserted the rotor blades 4.
  • the rotor blades 4 possess hammerhead-shaped bases 5 which are arranged obliquely to the rotor disk axis and in the assembled condition engage underneath the webs 6 of the tangential groove 3 and fill out the groove cross section.
  • the present invention will be explained now in detail hereinafter with reference to a rotor disk 2 of the rotor 1.
  • FIG. 2 illustrates an enlarged cross section through the outermost right rotor disk 2 of FIG. 1 with an inserted rotor blade 4 and the hammer-head-shaped base 5 thereof engaging underneath the webs 6 of the circumferential groove 3.
  • the base plate 7 of the rotor blade 4 terminates at the left upper edge 8 of the rotor disk 2.
  • the base plates 7 of the remaining rotor blades in the rotor disks 2a which on both sides thereof adjoin further rotor disks, terminate on both sides with the edges 8 of the rotor disk.
  • the rotor blade 4 is rotated, about its longitudinal axis by about 60-90 and is then inserted with its base 5 radially into the circumferential groove 3 of the rotor disk 2, is then turned back and thereafter displaced in the circumferential direction.
  • An aperture 9 is provided in the webs 6 of the tangential groove 3 for the insertion of the rotor blades 4 as can be seen from FIG. 3.
  • the base plates 7 of the blades 4 are pushed against one another and the hammerhead-shaped bases 5 which are shown in dash line have a constant spacing from one another.
  • the last blades 4 have been inserted into the tangential groove 3 of the rotor disk 2 and the base plates 7 have been displaced toward one another, there remains a residual gap having the length S. No blade can be inserted by rotation into this residual gap of the length S because the large diagonal of the base plate would no longer permit a rotation of the blade.
  • the base plates 7 are so reduced in size compared to the normal blades that the blades during the assembly operation are disposed closer to one another in the circumferential direction and thus result in the necessary gap for the insertion of the last blade, which can be seen in particular from FIGS. 5 and 8.
  • a transmitting element 10 for preventing movement of the blades in the circumferential direction is inserted also by rotation into the aperture 9 of the rotor disk 2.
  • the transmitting member 10 has essentially the same shape as the hammer-headshaped base 5 of a blade 4 and as a result of the rotation wedges or looks itself between the arcuateIy-shaped apertures 9 in the webs 6 of the tangential groove 3 of the rotor disk 2. An automatic rotating back of the transmitting element 10 is not possible since the blade bases 5 in the pushed together condition of the blades 4 abut against the lateral surfaces 11 of the transmitting member 10, in case a displacement should take place along the circumference of the rotor disk 2.
  • the base plates 7 cover the transmitting element 10 so that the transmitting element 10 is not visible in the assembled condition of the blades.
  • the radial height of the transmitting element is so selected that the transmitting element 10 forms approximately an end, i.e., is approximately flush with the upper edge of the web 6 of the tangential groove 3 and thereby results in a minimum of weight.
  • blades 4 can be seen in a plan view on the rotor disk 2 in FIG. 5, whose base plates are reduced in length either on both sides or on one side.
  • the base plates 7 of the rotor blades 4 illustrated in FIG. 3 for example, the base plates 12 of two rotor blades 4 illustrated in FIG. 5 are shortened on both sides with respect to the rotor blade and the base plate 13 of a rotor blade illustrated in FIG. 5 is shortened on one side thereof. That is, base plates 12 are shortened on both sides in the circumferential direction and base plate 13 is shortened only on one side thereof. 1
  • the filler elements 14 are divided centrally in a radial direction and possess in the assembled condition the outer contour of the blade base 5 with a base plate 7 and are also retained underneath the webs 6 of the groove 3.
  • the filler elements 14 are locked in the illustrated manner by mutual displacement and locking. After the filling in of the filler elements, the two blades 4 with base plates 12 short ened on both sides are moved apart from one another and the residual gap 15 resulting between the same is filled out by a locking element generally designated by reference numeral 16 (FIG. 8).
  • the lock 16 is illustrated in its initial shape in FIG. 7. It can be economically manufactured from sheet metal, for example,by spray-etching.
  • the sheet metal plate 17 can be transformed into the shape necessary for'the installation by bending together so that the lock 16 has the shape illustrated in FIGS. 8 and 9.
  • Tabshaped tongue portions 18 are provided at the upper edge., The lock 16 is now inserted into the residual gap 15 and is retained underneath the two adjacent base plates of the blades bya rotation so that it cannot fall out. Subsequently,the two lug-shaped tongue portions 18 are bent down which then adapt themselves to the gap shape of the gap 15 between the two blade base plates 12. The lock 16 thus cannot rotate back and furthermore the two adjacent blades cannot move any longer toward one another.
  • the two tab-like tongue portions 18 are so constructed in their length that they do not fill out completely the entire residual gap 15 and can again be bent upwardly at any time with a hookshaped tool and the lock can again be removed during .
  • a blade fastening arrangement according to claim 1, characterized in that said at least one locking element for the residual gap remaining in the assembled condition of the blade means is arrangedin the assembled condition transversely to the edges of the base plate means with portions engaging underneath the adjacent base plate means to prevent withdrawal thereof in a radial direction.
  • a blade fastening arrangement characterized in that the hammer-head-like base portions are arranged obliquely to the rotor disk axis and are adapted to be inserted by rotation into the groove means in such a manner that they fill nearly completely the groove cross-section.
  • a blade fastening for blade means of compressor or turbines retained in tangential groove means provided at the outer circumference of rotor diskmeans characterized in that the tangential groove means form web portions covering hammer-head-like base portions of the blade means substantially over the entire circumference of the rotor disk means, in that the blade means provided with the hammer-headlike base portions are adapted to be inserted radially 'into the tangential groove means provided with relatively small aperture means by rotation of the blade means about their longitudinal axis, in that means are provided for fixing the blade means in a predetermined position relative to the outer diameter of the disk means, in that transmitting means with rounded-off outer corners are provided as clamping means which are matched essentially to the base shape of the blade means and are retained in the aperture means by a wedging action, and in that the transmitting means terminate in the radial height thereof below base plate means provided on said blade means radially outwardly of said base portions and in the assembled condition are covered by the base plate means pushed against one another.
  • a blade fastening arrangement characterized in that some base plate means are shortened in the circumferential direction on at least one side in relation to the other blade means.
  • a blade fastening arrangement characterized in that the base plate means of the blade means inserted last are shortened in the circumferential direction at least on one side in relation to the other blade means.
  • a blade fastening arrangement characterized in that the base plate means of at least one blade means is shortened in the circumferential direction on one side in relation to other blade means and at least one other base plate means is shortened on both sides in relation to other blade means.
  • a blade fastening arrangement characterized in that an arcuately shaped aperture means is provided in mutually opposite web portions of the groove means for accommodating insertion of said at least one transmitting element.
  • a blade fastening arrangement characterized in that the blade means have a constant spacing from one another in the assembled condition and in that the gaps formed by the shortened base plate means are filled by filler means.
  • a blade fastening arrangement characterized in that the filler means are divided centrally in the radial direction and in the assembled condition possess substantially the outer contour of the blade base portion with base plate means and are retained underneath the web portions of the groove means.
  • a blade fastening arrangement characterized in that the cross-sectional shape of said at least one transmitting element is matched essentially to the shape of the base portions of the blade means.
  • a blade fastening arrangement characterized in that said at least one locking element for the residual gap remaining in the assembled condition of the blade means is arranged in the assembled condition transversely to the edges of the base plate means ,with portions engaging underneath the adjacent base plate means toprevent withdrawal thereof in a radial direction.
  • each of the at least one locking elements is formed of a bent, double sheet metal element and is provided at its upper edge with two tab-shaped tongue portions which are bent in the assembled condition of the locking element between the adjacent base plate means and fill the residual gap in its width.
  • a blade fastening arrangement according to claim 16 characterized in that said groove means is of dove-tail cross-sectional shape.
  • a blade fastening arrangement according to claim 20, characterized in that the blade means have a constant spacing from one another in the assembled condition and in that the gaps formed by the shortened base plate means are filled by filler means which are separate from the transmitting and locking means.
  • a blade fastening arrangement according to claim 19, characterized in that said transmitting, filler and locking means are provided several times symmetrically along the circumference of the rotor disk means.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00108350A 1970-01-21 1971-01-21 Blade mounting Expired - Lifetime US3778191A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2002469A DE2002469C3 (de) 1970-01-21 1970-01-21 Laufschaufelbefestigung in einer schwalbenschwanzförmigen Umfangsnut eines Läufers axial durchströmter Strömungsmaschinen, insbesondere Gasturbinenstrahltriebwerke

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US3778191A true US3778191A (en) 1973-12-11

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US00108350A Expired - Lifetime US3778191A (en) 1970-01-21 1971-01-21 Blade mounting

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US (1) US3778191A (OSRAM)
DE (1) DE2002469C3 (OSRAM)
FR (1) FR2075804A5 (OSRAM)
GB (1) GB1326122A (OSRAM)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
US4432697A (en) * 1981-04-10 1984-02-21 Hitachi, Ltd. Rotor of axial-flow machine
US4684326A (en) * 1982-08-16 1987-08-04 Terry Corporation Bladed rotor assembly, and method of forming same
US5360318A (en) * 1992-08-06 1994-11-01 Hitachi Ltd. Compressor for gas turbine and gas turbine
US20060083621A1 (en) * 2004-10-20 2006-04-20 Hermann Klingels Rotor of a turbo engine, e.g., a gas turbine rotor
US20060257248A1 (en) * 2005-02-23 2006-11-16 Rene Bachofner Rotor end piece
US20070134100A1 (en) * 2003-10-31 2007-06-14 Mtu Aero Engines Gmbh Turbine engine and bladed rotor for a compression stage of a turbine engine
CN101070858B (zh) * 2006-05-12 2012-08-08 斯奈克玛 一种飞机发动机压气机的轮盘-叶片装置
US20130170996A1 (en) * 2012-01-03 2013-07-04 General Electric Company Rotor blade mounting
US20140140849A1 (en) * 2012-11-21 2014-05-22 Solar Turbines Incorporated Gas turbine engine compressor rotor assembly and balancing system
US9828865B2 (en) 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
US20210254480A1 (en) * 2020-02-18 2021-08-19 United Technologies Corporation Tangential Rotor Blade Slot Spacer for a Gas Turbine Engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119026B (en) * 1981-03-25 1984-06-20 Rolls Royce Aerofoil blade mounting
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement
DE102004011508A1 (de) * 2004-03-08 2005-09-29 Alstom Technology Ltd Rotor-Schluss

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US995367A (en) * 1909-03-01 1911-06-13 Allis Chalmers Steam-turbine.
US1539574A (en) * 1922-04-18 1925-05-26 Westinghouse Electric & Mfg Co Turbine-blade fastening
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
US3053504A (en) * 1960-01-18 1962-09-11 Rolls Royce Method of assembling a bladed member
GB916001A (en) * 1961-02-09 1963-01-16 Prvni Brnenska Strojirna Improvements in or relating to rotors for turbines and compressors
US3216700A (en) * 1963-10-24 1965-11-09 Gen Electric Rotor blade locking means

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US995367A (en) * 1909-03-01 1911-06-13 Allis Chalmers Steam-turbine.
US1539574A (en) * 1922-04-18 1925-05-26 Westinghouse Electric & Mfg Co Turbine-blade fastening
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
US3053504A (en) * 1960-01-18 1962-09-11 Rolls Royce Method of assembling a bladed member
GB916001A (en) * 1961-02-09 1963-01-16 Prvni Brnenska Strojirna Improvements in or relating to rotors for turbines and compressors
US3216700A (en) * 1963-10-24 1965-11-09 Gen Electric Rotor blade locking means

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
US4432697A (en) * 1981-04-10 1984-02-21 Hitachi, Ltd. Rotor of axial-flow machine
US4684326A (en) * 1982-08-16 1987-08-04 Terry Corporation Bladed rotor assembly, and method of forming same
US5360318A (en) * 1992-08-06 1994-11-01 Hitachi Ltd. Compressor for gas turbine and gas turbine
US20070134100A1 (en) * 2003-10-31 2007-06-14 Mtu Aero Engines Gmbh Turbine engine and bladed rotor for a compression stage of a turbine engine
US7399164B2 (en) * 2003-10-31 2008-07-15 Mtu Aero Engines Gmbh Turbine engine and bladed rotor for a compression stage of a turbine engine
US7708529B2 (en) 2004-10-20 2010-05-04 Mtu Aero Engines Gmbh Rotor of a turbo engine, e.g., a gas turbine rotor
EP1650405A1 (de) * 2004-10-20 2006-04-26 MTU Aero Engines GmbH Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
US20060083621A1 (en) * 2004-10-20 2006-04-20 Hermann Klingels Rotor of a turbo engine, e.g., a gas turbine rotor
US20060257248A1 (en) * 2005-02-23 2006-11-16 Rene Bachofner Rotor end piece
US7367778B2 (en) * 2005-02-23 2008-05-06 Alstom Technology Ltd. Rotor end piece
CN101070858B (zh) * 2006-05-12 2012-08-08 斯奈克玛 一种飞机发动机压气机的轮盘-叶片装置
JP2013139769A (ja) * 2012-01-03 2013-07-18 General Electric Co <Ge> ロータブレード装着システム
US20130170996A1 (en) * 2012-01-03 2013-07-04 General Electric Company Rotor blade mounting
US8899933B2 (en) * 2012-01-03 2014-12-02 General Electric Company Rotor blade mounting
EP2612999A3 (en) * 2012-01-03 2017-03-29 General Electric Company Blade mounting system
US9828865B2 (en) 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
US20140140849A1 (en) * 2012-11-21 2014-05-22 Solar Turbines Incorporated Gas turbine engine compressor rotor assembly and balancing system
US9404367B2 (en) * 2012-11-21 2016-08-02 Solar Turbines Incorporated Gas turbine engine compressor rotor assembly and balancing system
RU2660981C2 (ru) * 2012-11-21 2018-07-11 Соулар Тербинз Инкорпорейтед Ротор компрессора в сборе газотурбинного агрегата с системой уравновешивания
US20210254480A1 (en) * 2020-02-18 2021-08-19 United Technologies Corporation Tangential Rotor Blade Slot Spacer for a Gas Turbine Engine
US11242761B2 (en) * 2020-02-18 2022-02-08 Raytheon Technologies Corporation Tangential rotor blade slot spacer for a gas turbine engine

Also Published As

Publication number Publication date
DE2002469C3 (de) 1978-03-30
DE2002469B2 (de) 1977-08-11
FR2075804A5 (OSRAM) 1971-10-08
GB1326122A (en) 1973-08-08
DE2002469A1 (de) 1971-07-29

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