US2727716A - Bladed body - Google Patents

Bladed body Download PDF

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Publication number
US2727716A
US2727716A US716930A US71693046A US2727716A US 2727716 A US2727716 A US 2727716A US 716930 A US716930 A US 716930A US 71693046 A US71693046 A US 71693046A US 2727716 A US2727716 A US 2727716A
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US
United States
Prior art keywords
blade
rotor
blades
root
tilting
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
US716930A
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English (en)
Inventor
Feilden Geoffrey Bertra Robert
Ogston Walter Mactavish
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.)
Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
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Publication of US2727716A publication Critical patent/US2727716A/en
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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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to improvements in the mounting of rotor blades in axial flow compressors, turbines, or similarly bladed fluid flow machines and has particular although not exclusive application to the case of axial flow units of this kind,,when used to deal with gaseous fluids in gas turbine engines for aircraft.
  • the present invention aims at enabling compensation of the kind indicated, in an axial flow compressor, turbine or similarly bladed machine, to be effectivelover a range of operating conditions, with the consequent advantage of also enabling the blades to be of much smaller chord than otherwise would be the case so long as this range is not exceeded, since the fluid loading may then be disregarded, or with a correspondingly smaller advantage if the range is exceeded.
  • the invention accordingly provides, in an axial flow compressor, turbine, or similarly bladed fluid flow ma- Chine having axial flow rotor blades so arranged that in the co'nditions of operation the centrifugal and fluid loads impose opposing bending moments thereon, and especially in a high speed machine of this kind operating with 4 more" specifically, each blade may have a pivot extending in the axial sense of the rotor, although notnecessarily in the.
  • each blade may be mounted for tilting by means of a guide bearing of arcuate cross section and preferably (in order to allow tilting in more than one plane) part spherical form; or again each blade may be rendered tiltable by being anchored by means of a flexible radially extending tension element in the natureof a strip or arod or wire.
  • tilting is provided for by the inclusion in each blade mounting of a pad of a material capable of yielding locally under stress by undergoing displacement analogous to hydraulic flow.
  • Materials such as rubber are suitable for this purpose, but in this connection a further feature of the invention consists in the use of a material which, though resilient, has a low response rate so that it does not respond to high frequency vibrations; that is, its acts to damp such vibrations. Synthetic rubber is found to be better for this purpose than the natural variety.
  • Figure l is a view in axial section of the rotor
  • Figure 2 an enlargement on section 2-2 of Figure 1 and Figure 3 a sectionon line 3-3 of Figure 2 showing one form of the invention.
  • Figures 4, 5 and 6 are views in axial, peripheral, and plan section respectively of a second form of the invention
  • Figures 7, 8 and 9 are an axial, peripheral and plan section respectively of a third form of the invention.
  • Figure 10 is-a fragmentary perspective'view of the blade" root of yet another form of the invention and Figure ll is a detail of Figure 10.
  • Figures 1' to 3 illustrate'a case in which rotor blades are rendered tiltable by being mounted on an axially extending pivot pin.
  • the complete rotor is built up from a plurality of discs 1, which are presumed to be held together axially by means which for the purposes of the present invention need not beconsidered.
  • Each disc 1 has a peripheral flange 2 and the axially successive rows or stages of blades 3 have their roots 4 located between and by the adjacent flanges 2 of successive discs.
  • the blades 3 are pivotally mounted through needle roller bearings 5 on pins 6 extending axially of the rotor and' passing through appropriate bores" of the blade roots 4, the ends of thepins' 6 being held in recesses in the flanges" 2 of the respective discs 1.
  • a periprs eral clearance is left. between adjacent blades is the same stage, so that each blade is capable! of tilting peripherally to adjust itself to variations in the relationship between gas and centrifugal load.
  • the pins 6 could be skewed with reference to the axial plane instead of being parallel with the axis of rotation.
  • the centre portion of the bore may be provided, as shown, with a widened part at 7 so that the mid point of the arc formed by each needle roller does not come into contact with the wall of the bore and thus foul the root.
  • Part of the root may also be cut away as shown at the left hand side of Figure 1 and in Figure 3, in order to economise in material and weight.
  • FIGs 4 and 5 illustrate in axial and peripheral section, and Figure 6 in section on line 6-6 of Figure 4, a modification in which the blade root 4 is anchored by means of a flexible radial tension strip 8 which for securing purposes is bent at one end round a pin 9 within the body of the root and at the other round a pin 10; As in the previous case, this pin extends axially, but may alternatively be skewed, and enters recesses in the adjacent flanges 2 of successive discs 1. Tilting of each blade is limited by the clearance between it and the one adjacent, as seen in Figure 3.
  • Figures 7, 8, and 9 illustrate in fragmentary axial section, circumferential section, and plan respectively an arrangement in which the pivot about which tilting takes place is defined by a spherical guide bearing, so that tilting may take place in more than one plane.
  • the spherical guide bearing is defined on the one hand by'a part-spherical head 11 screwed or otherwise secured to a shank 12 on the blade root, and on the other by part-spherical recesses formed in the members 14 which lie between the rotor discs 1 and provide a hole for the passage of the blade shanks 12.
  • a ball race 15 is disposed in the spherical bearing space between the head 11 and each member 14, and tilting of the blades both circumferentially and axially is permitted by appropriate clearances as indicated between each blade and adjacent blades and the rotor parts.
  • the clearance between adjacent blades in principle, also allows rotation of the blades about radial axes, but by keeping the clearances low and the interengaging faces long in the axial direction such rotation can be rendered negligible.
  • each blade may be bedded on a pad of yielding material as illustrated in the fragmentary perspective view of Figure 10.
  • the blade root consists of a rectangular base 16 having a channel 17 running round its sides in which is accommodated a pad 18 of yielding material (separately shown in Figure 11), the shaping and dimensioning of which is such as to leave in the channel 17 at the upstream and downstream sides of the base 16 a recess into which fit correspondingly shaped lips 19 on the adjacent rotor discs 1.
  • tilting may take place in the peripheral direction a clearance is left between the blades, but it will be apparent that the direction of tilt can also have a component in the axial plane.
  • the yielding material should be one such as rubber which is enabled to yield locally by undergoing displacement analogous to hydraulic flow and preferably also, whilst being resilient, should be selected to have a low response and recovery rate so that it does not yield under the influence of high frequency vibrations such as may be encountered in compressor and like blading, but does yield to a sustained load. In this way, not only is the desired compensating tilt obtainable when there is a change in the gas load/centrifugal force ratio, but also the mounting acts as a vibration damper.
  • synthetic rubber is found to have better characteristics than the natural variety.
  • An axial flow compressor, turbine or similarly bladed fluid flow machine in which the blades are short in length compared with the diameter of the rotor comprising a rotor having in its peripheral surface blade retaining recesses, each formed with a pair of tongues projecting towards one another from opposite faces of said recess, a plurality of blades distributed in uniformly spaced relationship around said rotor surface in said recesses, each blade and blade root being spaced from its adjacent blade and blade root and with the root mounting of each of said blades formed with a pair of grooves on opposite sides thereof for reception and engagement therein on said pair of tongues with radial clearance between said tongues and grooves and a plurality of shaped pads of rubber or similar material capable of yielding locally under load with displacement of material and capable of returning to shape on removal of load located with said tongues in said grooves to fill said radial clearance completely and hold said blades securely mounted individually and independently of any other support on said rotor for tilting movement under centrifugal and fluid loads and render each self positionmg.
  • An axial flow compressor, turbine or similarly bladed fluid flow machine in which the blades are short in length compared with the diameter of the rotor comprising a rotor having at least one blade retaining recess circumferentially arranged around the periphery of said rotor with a pair of tongues projecting towards one another from opposite faces of said recess, a plurality of blades distributed in uniformly spaced relationship around said rotor in said recess and with their root mountings of rectangular form, each blade and blade root being spaced from its adjacent blade and blade root, and provided with a groove formed'thereon disposed around the four sides and with portions on opposite sides formed for reception of and engagement therein of said pair of tongues with radial clearance, and a plurality of shaped pads of rubber or similar material capable of yielding locally under load with displacement of material and capable of returning to shape on removal of load, each formed as a thin rectangular body with a rectangular hole for location in a said groove on each side of said rectangular root mountings to fill said radial clearance completely and
  • An axial flow compressor, turbine or similarly bladed fluid flow machine in which the blades are short in length compared with the diameter of the rotor comprising a rotor having at least one blade retaining recess circumferentially arranged around the periphery of said rotor with a pair of tongues projecting towards one another from opposite faces of said recess, a plurality of blades distributed in uniformly spaced relationship around said rotor in said recess, each blade and blade root being spaced from its adjacent blade and blade root mounting and having its root mounting formed with an annular groove for reception and engagement of said pair of tongues with radial clearance and a plurality of annular pads of rubber or similar material capable of yielding locally under load with displacement of material and capable of returning to shape on removal of load, each located in a said annular groove on each of said root mountings to fill said radial clearance completely and hold said blades securely mounted individually and independently of any other support on said rotor for tilting movement vunder centrifugal and fluid loads and render each self positioning.
  • An axial flow compressor, turbine or similarly bladed fluid flow machine comprising a rotor having in its peripheral surface blade retaining recesses each formedwith tongues projecting towards one another from opposite faces of said recesses, a plurality of blades distributed in uniformly spaced relationship around the periphery of said rotor, each of said blades terminating in a root located in one of said recesses, each blade and blade root being spaced from its adjacent blade and blade root, each of said roots being formed with grooves to receive said tongue with clearance, each said groove being deeper than the said tongue therein by a distance which would allow the root to move radially outward for some distance through a radial clearance space, and a plurality of resilient pads of rubbery material each shaped to fit in and fill one of said radial clearance spaces completely and to clamp said blade root between the pad and said tongue and hold said blade securely individually and independently of any other support of said rotor for tilting movement under centrifugal and fluid loads on each blade.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US716930A 1945-12-21 1946-12-18 Bladed body Expired - Lifetime US2727716A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB264413X 1945-12-21

Publications (1)

Publication Number Publication Date
US2727716A true US2727716A (en) 1955-12-20

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Family Applications (1)

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US716930A Expired - Lifetime US2727716A (en) 1945-12-21 1946-12-18 Bladed body

Country Status (6)

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US (1) US2727716A (sv)
BE (1) BE470026A (sv)
CH (1) CH264413A (sv)
FR (1) FR937883A (sv)
GB (1) GB606151A (sv)
NL (1) NL70700C (sv)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
US2978168A (en) * 1954-12-06 1961-04-04 Relle Royce Ltd Bladed rotor for axial-flow fluid machine
DE1167852B (de) * 1962-08-10 1964-04-16 Bbc Brown Boveri & Cie Schwingungdaempfende Laufschaufelbefestigung bei Axialturbomaschinen
US3687569A (en) * 1971-03-19 1972-08-29 Gen Electric Rotor with variable angle blades
US4022545A (en) * 1974-09-11 1977-05-10 Avco Corporation Rooted aerodynamic blade and elastic roll pin damper construction
EP2644828A1 (de) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modulare Turbinenschaufel mit Plattform
WO2014049280A2 (fr) 2012-09-28 2014-04-03 Snecma Attache auto-serrante pour aube de turbine en cmc
US20150064018A1 (en) * 2012-03-29 2015-03-05 Siemens Aktiengesellschaft Turbine blade and associated method for producing a turbine blade
US20200072063A1 (en) * 2018-08-31 2020-03-05 Rolls-Royce Corporation Pinned platform for blade with circumferential attachment
US11326474B2 (en) * 2019-12-04 2022-05-10 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE501031A (sv) * 1950-02-03
US2819869A (en) * 1950-05-02 1958-01-14 Jr Andre J Meyer Mounting arrangement for turbine or compressor blading
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
NL81240C (sv) * 1951-08-31 1955-11-15
US2819871A (en) * 1954-09-07 1958-01-14 John R Mcveigh Vane structure
US2919889A (en) * 1955-03-03 1960-01-05 United Aircraft Corp Blade mounting
US3984194A (en) * 1974-04-12 1976-10-05 Aktiebolaget Svenska Flaktfabriken Axial flow fans

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB302953A (en) * 1927-09-21 1928-12-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
US1802648A (en) * 1925-12-31 1931-04-28 American Propeller Company Propeller
US1921931A (en) * 1930-01-23 1933-08-08 Levasseur Pierre Screw propeller
US2219288A (en) * 1936-01-13 1940-10-29 Harold T Avery Rotative wing aircraft
US2235605A (en) * 1937-03-10 1941-03-18 Bugatti Ettore Screw propeller
US2240873A (en) * 1937-11-11 1941-05-06 Dehavilland Aircraft Mounting of airscrew blades
DE713187C (de) * 1936-11-07 1941-11-03 Siemens Schuckertwerke Akt Ges Befestigung fuer ein Luefterrad auf seiner Antriebswelle
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2344266A (en) * 1941-06-27 1944-03-14 Reissner Hans Aircraft propeller construction
US2354101A (en) * 1942-08-07 1944-07-18 United Aircraft Corp Fan construction
US2394460A (en) * 1939-07-04 1946-02-05 Martinotti Pietro Aircraft propeller
US2416178A (en) * 1944-09-19 1947-02-18 United Aircraft Corp Resiliently hinged blade mounting
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
US2473899A (en) * 1943-12-11 1949-06-21 Curtiss Wright Corp Articulated and universal joint for propellers and other mechanisms
US2595829A (en) * 1946-12-19 1952-05-06 Benson Mfg Company Axial flow fan and compressor

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1802648A (en) * 1925-12-31 1931-04-28 American Propeller Company Propeller
GB302953A (en) * 1927-09-21 1928-12-21 Neil Shaw Muir Improvements in or relating to centrifugal blowers, compressors and the like
US1921931A (en) * 1930-01-23 1933-08-08 Levasseur Pierre Screw propeller
US2219288A (en) * 1936-01-13 1940-10-29 Harold T Avery Rotative wing aircraft
DE713187C (de) * 1936-11-07 1941-11-03 Siemens Schuckertwerke Akt Ges Befestigung fuer ein Luefterrad auf seiner Antriebswelle
US2235605A (en) * 1937-03-10 1941-03-18 Bugatti Ettore Screw propeller
US2240873A (en) * 1937-11-11 1941-05-06 Dehavilland Aircraft Mounting of airscrew blades
US2394460A (en) * 1939-07-04 1946-02-05 Martinotti Pietro Aircraft propeller
US2344266A (en) * 1941-06-27 1944-03-14 Reissner Hans Aircraft propeller construction
US2317338A (en) * 1942-02-07 1943-04-20 Westinghouse Electric & Mfg Co Turbine blade fastening apparatus
US2354101A (en) * 1942-08-07 1944-07-18 United Aircraft Corp Fan construction
US2473899A (en) * 1943-12-11 1949-06-21 Curtiss Wright Corp Articulated and universal joint for propellers and other mechanisms
US2416178A (en) * 1944-09-19 1947-02-18 United Aircraft Corp Resiliently hinged blade mounting
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
US2595829A (en) * 1946-12-19 1952-05-06 Benson Mfg Company Axial flow fan and compressor

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
US2978168A (en) * 1954-12-06 1961-04-04 Relle Royce Ltd Bladed rotor for axial-flow fluid machine
DE1167852B (de) * 1962-08-10 1964-04-16 Bbc Brown Boveri & Cie Schwingungdaempfende Laufschaufelbefestigung bei Axialturbomaschinen
US3687569A (en) * 1971-03-19 1972-08-29 Gen Electric Rotor with variable angle blades
US4022545A (en) * 1974-09-11 1977-05-10 Avco Corporation Rooted aerodynamic blade and elastic roll pin damper construction
EP2644828A1 (de) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modulare Turbinenschaufel mit Plattform
WO2013144270A1 (de) * 2012-03-29 2013-10-03 Siemens Aktiengesellschaft Modulare turbinenschaufel mit plattform
US20150064018A1 (en) * 2012-03-29 2015-03-05 Siemens Aktiengesellschaft Turbine blade and associated method for producing a turbine blade
WO2014049280A3 (fr) * 2012-09-28 2014-09-12 Snecma Attache auto-serrante pour aube de turbine en cmc
FR2996251A1 (fr) * 2012-09-28 2014-04-04 Snecma Attache auto-serrante pour aube de turbine en cmc
WO2014049280A2 (fr) 2012-09-28 2014-04-03 Snecma Attache auto-serrante pour aube de turbine en cmc
CN104685162A (zh) * 2012-09-28 2015-06-03 斯奈克玛 用于cmc涡轮叶片的自夹紧紧固件
JP2015530518A (ja) * 2012-09-28 2015-10-15 スネクマ Ｃｍｃタービンブレード用の自己固定型ファスナ
CN104685162B (zh) * 2012-09-28 2017-04-12 斯奈克玛 用于cmc涡轮叶片的自夹紧紧固件
RU2664752C2 (ru) * 2012-09-28 2018-08-22 Снекма Лопатка турбины, диск рабочего колеса турбины и турбомашина
US10227881B2 (en) 2012-09-28 2019-03-12 Safran Aircraft Engines Self-clamping fastener for CMC turbine blade
US20200072063A1 (en) * 2018-08-31 2020-03-05 Rolls-Royce Corporation Pinned platform for blade with circumferential attachment
US11156111B2 (en) * 2018-08-31 2021-10-26 Rolls-Royce Corporation Pinned platform for blade with circumferential attachment
US11326474B2 (en) * 2019-12-04 2022-05-10 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting

Also Published As

Publication number Publication date
BE470026A (sv)
NL70700C (sv)
GB606151A (en) 1948-08-06
FR937883A (fr) 1948-08-30
CH264413A (de) 1949-10-15

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