US3734645A - Turbine blade assembly - Google Patents

Turbine blade assembly Download PDF

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Publication number
US3734645A
US3734645A US00097105A US3734645DA US3734645A US 3734645 A US3734645 A US 3734645A US 00097105 A US00097105 A US 00097105A US 3734645D A US3734645D A US 3734645DA US 3734645 A US3734645 A US 3734645A
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Prior art keywords
blades
blade
rings
faces
array
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Expired - Lifetime
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US00097105A
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English (en)
Inventor
R Strub
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Brown Boveri Sulzer Turbomaschinen AG
Sulzer Escher Wyss AG
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Brown Boveri Sulzer Turbomaschinen AG
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Assigned to SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND reassignment SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR
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Expired - Lifetime legal-status Critical Current

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    • 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

Definitions

  • the blades of a blade row in a turbine or similar machine possess roots having two pairs of opposite faces and are disposed in an annular array with the help of wedge-shaped spacers between the roots of adjacent blades.
  • the blade root faces of one of these pairs define at each axial end of the array an annular stepped or sawtooth-shaped surface, according to the angular orientation of the blades about their individual longitudinal axes, and the blades are held in a selected orientation by means of rings having mating annular stepped or sawtooth-shaped surfaces thereon.
  • turbomachine is used to denote a turbine-type machine whether for development of mechanical energy at a rotating shaft from a fluid flowing through the machine as in a turbine, or for the delivery of energy from a rotating shaft to the fluid, as in a pump or compressor.
  • the pitch changing mechanism is coupled to control apparatus so as to keep the blades set to the pitch which is optimum for the existing load. If however substantial changes in load occur only infrequently, means to permit adjustment in blade pitch while the machine is in operation can be dispensed with. It is then customary to provide blades which can be reset in pitch, at the roots thereof, only when the machine is brought to rest and with at least partial disassembly of the machine to make the rotor accessible. If the time intervals in operation can be dispensed with.
  • Blades which are rotatable at the roots thereof for pitch change have the disadvantage that they can come loose in operation, especially when subjected to large temperature changes, with consequent possibility of severe damage to the machine. On the other hand when no provision is made for change of blade pitch, change of the blading is extremely costly.
  • the blade roots include a portion of quadrilateral shape. This portion has two faces which may be parallel to each other and to the long dimension of the blade and which are approximately parallel to the chord of the blade. With the help of wedge-shaped inserts between adjacent blade roots which engage the blade roots at these faces, the blade roots of an assembled blade row make up a ring, in which however these faces typically do not lie in planes containing the axis of symmetry of the ring or ring-shaped array but are instead skewed with respect to that axis.
  • Each blade root includes two additional faces which may be parallel to each other and to the long dimension of the blade and which may be perpendicular to the pair of faces first mentioned.
  • the faces of this second pair usually are not perpendicular to the ring axis but instead are also skewed with respect thereto.
  • the blades of a row are held together in a ring-shaped array by means of two rings each having an end face notched or otherwise shaped to match the circular sawtooth surface defined at each axial end of the array of blades by the secondmentioned lateral faces of the blade roots.
  • FIG. I is a fragmentary axial sectional view through a blade assembly in accordance with the present inventlon
  • FIG. 2 is a fragmentary radially inwardly directed developed view of the blade assembly of FIG. 1;
  • FIG. 3 is a fragmentary radially outwardly directed developed sectional view of the blade assembly of FIG. 1, taken on the line IIIIII of FIG. 1;
  • FIG. 4 is a fragmentary perspective view of the assembly of FIGS. 1 to 3 in partially assembled condition, showing two blades, their adjacent wedge-shaped spacers, and one of the end rings;
  • FIG. 5 is a further figure similar to that of FIG. 2 but illustrating a modified construction according to the invention in which the end rings are provided with axially directed pins instead of notches for the purpose of holding the blades at a desired pitch; and
  • FIG. 6 is still another figure similar to that of FIG. 2 but illustrating still another embodiment in which the rings are provided with radially directed pins having a portion of conical shape to define sawtooth-shaped surfaces to hold the blades of the row in a desired pitch setting.
  • the turbine blade assembly illustrated in FIGS. 1 to 4 comprises a single row of blades each generally indicated at the reference character 1.
  • the blades are disposed on a circumferential interval 1? measured either angularly or linearly, for example at the root end of the blades proper.
  • this interval is sometimes termed blade pitch, the term pitch is not so used herein, but is used instead to denote the angular orientation of the individual blades about their longitudinal axes, which extend radially of the machine.
  • the blade proper 2 and the root 3 (FIG. 1) of each blade form an integral whole and are hence fixed in position with respect to each other.
  • the blade root 3 includes a portion having a quadrilateral section, as indicated by the closely hatched areas in FIG. 3. This portion is, on each blade, bounded by two first faces 4 which may be parallel to each other and to the long dimension of the blade and which are approximately parallel to the chord of the blade, indicated at 5 in FIG. 2. As illustrated in FIG. 4, it is at these faces 4 that the roots of adjacent blades bear against each other in the blade assembly of the invention, with the interposition of wedge-shaped spacers 8.
  • these faces 4 do not lie in meridian planes 'of the assembly, i.e., in planes containing the axis of symmetry of the assembly, but rather in planes skew thereto.
  • the face 4 seen in FIG. 1 will not lie in the plane of that figure, but will be inclined to it instead.
  • the quadrilateral portion of the blade root is bounded by two additional faces 6, desirably also parallel to the long dimension of the blade proper and to each other but transverse (e.g. perpendicular) to the faces 4.
  • these faces 6 are skewed to the axis of symmetry of the assembly, and hence present a sawtooth surface formed into a circle, much like that of the teeth on a crown saw. This is seen in FIG. 4 at the exposed faces 6 of two adjacent blades.
  • end rings and 11 are provided, each having one face having a sawtooth shape matching or substantially matching the ring-shaped sawtooth surface presented by one of the sets of end faces 6 of the blade roots.
  • the construction of one of these rings, namely the ring 11, is shown in the fragmentary perspective view of FIG. 4.
  • the sawtooth-shaped surface at each axial end of the row of blade roots includes an axial end face of each of the wedges 8. More over, the sawtooth-shaped surface on the blade row at one axial end of the blade row (the end near the reader in FIG. 4) includes a part of one face 4 from each of the blade roots whereas the sawtooth-shaped surface on the blade row at the opposite axial end of the blade row includes a part of one of the slant faces on each of the wedges.
  • Each blade root may include, in the case of a row of radially outwardly extending blades such as the rotor blades in FIGS. 1 to 4, an axial extension 9 over which one of the rings 10 and 11 extends, to impose on the blades during rotation the central acceleration necessary to hold them in the assembly.
  • Other blade anchoring arrangements can of course be employed consistently with the invention.
  • the blades may be fixed in position in a turbine housing, of which the ring may form a part or to which it may be fastened, and can consequently operate to deflect the flow of a working fluid either at the inlet or at the outlet of rotor blade rows in axial turbines or compressors.
  • the angle a (as shown in FIGS. 2, 5 and 6) must be reduced in value and vice versa.
  • the rings 10 and 11 must be replaced with new rings having notches corresponding to the desired altered value of the angle a.
  • the spacers 8 also makes it necessary to replace the spacers 8 since the separation of the side faces 4 of adjacent blade roots will be smaller or larger, as will also be the angular separation of those faces.
  • the circumferential blade inter val 2 (FIG. 2) remains unchanged. Notwithstanding the constancy of the circumferential blade interval t, the flow cross-section varies with pitch setting between minimum and maximum values, for a given number of blades in the row. The maximum value can be increased if one or more blades are removed from the row, the larger spacing between blade roots thus permitted being filled up by spacer elements 8. It is thus possible, without changing the total flow-through capacity of the blade row, to vary over a range of values the angle of attack for the working substance through the blade row.
  • rings 20 and 21 which may have smooth faces but which are provided each with a set of axially extending pins 22, one for each blade of the row.
  • the pins desirably have rounded ends, as indicated in the phantom view of FIG. 5.
  • the pins are desirably threaded into their rings so as to be axially adjustable. These pins extend into the notches of the saw-toothed surfaces provided by the faces 6 of the blade roots, and thereby serve to hold the blades of a row in fixed relative position.
  • the angle a it is in such an embodiment necessary only to adjust the position of the pins 22 in their rings 20 or 21 and to dispose between the blade roots replacement spacer elements or wedges 86 of changed dimension corresponding to the new angle a and themselves of properly corrected wedge angle.
  • the pins can be prevented from undesired creeping or turning by provision of a suitably eccentric surface on the heads thereof against which'the blade roots will bear.
  • FIG. 6 illustrates still a further embodiment employing radially extending bolts or pins 32 to provide on end rings 30 and 31 the equivalent of the sawtooth-shaped surface seen on the ring 11 of FIG. 4.
  • These pins 32 may advantageously have a conical shape helping to define for their ring a sawtooth-shaped surface similar to that of the ring 11 of FIG. 4.
  • the shape of the bolts 32 must of course be adjusted to the desired angle a and also to the circumferential interval of the blading. For changing the pitch of a blade row in such an embodiment it is necessary only to change the bolts 32 which themselves make up then the saw-toothed surface on the rings, and also the spacers 87.
  • Blade assemblies according to the invention can be employed in blowers, compressors and turbines and are especially useful in axial-flow and single-stage machines.
  • the invention thus provides a blade assembly for a turbomachine comprising a plurality of blades disposed in an annular array.
  • the blades have roots including a portion having two opposite sides as shown at 4 in the drawings, and spacer elements are disposed between circumferentially adjacent ones of the blade roots. Adjacent of these spacer elements engage these two opposite sides on the root of a blade.
  • the blade roots include at least one and preferably two additional sides, as indicated at 6 in the drawings, extending transversely of the sides 4.
  • Two rings are provided, and at least one of these includes means to define thereon end surface substantially matching the annular sawtooth-shaped surface presented by the sum of those additional sides on the blade roots facing in one direction axially of the array.
  • the blade roots may have more than four sides, and the end rings may be provided with more complex sawtooth surfaces to match them.
  • a blade assembly for a turbomachine comprising a plurality of blades disposed in an annular array, said blades having each a root including a portion of quadrilateral crosssection having two first opposed faces skewed to the axis of the array, spacer elements between circumferentially adjacent ones of said blade roots, adjacent of said spacer elements engaging said first opposed faces on one of said blade roots, said blade root portions having each two additional opposed faces extending transversely of said first opposed faces, said additional faces being skewed to the axis of the array, whereby said blade roots and spacer elements constitute an annular array having two sawtooth-shaped end faces, two rings on axially opposed sides of the array, each of said rings including means to define adjacent said array an annular sawtoothed-shaped surface of which the teeth extend axially of the array and are equal in number to said plurality, each tooth on one of said rings engaging the root of one of said blades at one of said first opposed faces and also engaging the root of a circumferentially adjacent one of
  • a blade assembly according to claim 1 wherein said means comprise an annular sawtooth-shaped surface on each of said rings.
  • a blade assembly according to claim 1 wherein said means comprise on each of said rings a plurality of axially extending pins, one for each of said blades.
  • a blade assembly according to claim 1 wherein said means comprise on each of said rings a plurality of conical radially directed bolts, one for each of said blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00097105A 1969-12-12 1970-12-11 Turbine blade assembly Expired - Lifetime US3734645A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1850069A CH516731A (de) 1969-12-12 1969-12-12 Schaufelkranz für Turbomaschinen

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US3734645A true US3734645A (en) 1973-05-22

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US00097105A Expired - Lifetime US3734645A (en) 1969-12-12 1970-12-11 Turbine blade assembly

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US (1) US3734645A (enrdf_load_html_response)
BE (1) BE760151A (enrdf_load_html_response)
CH (1) CH516731A (enrdf_load_html_response)
DE (1) DE1963922C3 (enrdf_load_html_response)
FR (1) FR2072221A5 (enrdf_load_html_response)
GB (1) GB1296791A (enrdf_load_html_response)
NL (1) NL7000530A (enrdf_load_html_response)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
WO2001071165A1 (de) 2000-03-23 2001-09-27 Alstom (Switzerland) Ltd Befestigung der beschaufelung einer strömungsmaschine
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
EP1707747A1 (de) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Schaufelfussbefestigung und entsprechendes Montageverfahren
RU2296227C1 (ru) * 2005-08-18 2007-03-27 Открытое Акционерное Общество "Теплоэнергосервис-ЭК" (ОАО "Теплоэнергосервис-ЭК") Узел соединения лопаток с ротором турбомашины (варианты)
US20080003098A1 (en) * 2004-12-21 2008-01-03 Alstom Technology Ltd. Method for modification of a turbocompressor
US20090110553A1 (en) * 2007-10-30 2009-04-30 Min-I Wu Omnidirectional electric fan and fan blade structure

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1160529B (it) * 1983-03-09 1987-03-11 Cofimco Srl Mozzo porta-pale per ventilatore assiale
DE102010002520A1 (de) * 2010-03-02 2011-09-08 Bernhard Unterlercher Turbinenrad mit stoff- und formschlüssig verbundenen Schaufeln

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US894659A (en) * 1906-12-29 1908-07-28 Gen Electric Bucket-wheel for turbines.
US1133191A (en) * 1913-11-29 1915-03-23 Hersey Staples Screw-propeller.
US1156529A (en) * 1914-06-10 1915-10-12 Gen Electric Turbine bucket-wheel.
US1590328A (en) * 1923-08-13 1926-06-29 Westinghouse Electric & Mfg Co Fastening means for turbine blading
FR863755A (fr) * 1939-09-25 1941-04-09 Rateau Soc Roues à ailettes pour turbo-machines
GB614074A (en) * 1946-07-02 1948-12-09 Aubrey Lawrence Collins Improvements in or relating to fans
DE872816C (de) * 1951-05-13 1953-04-09 Benno Schilde Maschb A G Nabe fuer Schraubenluefterrad
US2918255A (en) * 1957-03-15 1959-12-22 Westinghouse Electric Corp Elastic fluid utilizing apparatus
US2925997A (en) * 1953-05-27 1960-02-23 Rolls Royce Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means
US3076633A (en) * 1955-06-28 1963-02-05 Parsons & Marine Eng Turbine Turbine and like rotor blades
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
US3096074A (en) * 1960-12-06 1963-07-02 Rolls Royce Bladed rotors of machines such as gas turbines

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US894659A (en) * 1906-12-29 1908-07-28 Gen Electric Bucket-wheel for turbines.
US1133191A (en) * 1913-11-29 1915-03-23 Hersey Staples Screw-propeller.
US1156529A (en) * 1914-06-10 1915-10-12 Gen Electric Turbine bucket-wheel.
US1590328A (en) * 1923-08-13 1926-06-29 Westinghouse Electric & Mfg Co Fastening means for turbine blading
FR863755A (fr) * 1939-09-25 1941-04-09 Rateau Soc Roues à ailettes pour turbo-machines
GB614074A (en) * 1946-07-02 1948-12-09 Aubrey Lawrence Collins Improvements in or relating to fans
DE872816C (de) * 1951-05-13 1953-04-09 Benno Schilde Maschb A G Nabe fuer Schraubenluefterrad
US2925997A (en) * 1953-05-27 1960-02-23 Rolls Royce Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means
US3076633A (en) * 1955-06-28 1963-02-05 Parsons & Marine Eng Turbine Turbine and like rotor blades
US2918255A (en) * 1957-03-15 1959-12-22 Westinghouse Electric Corp Elastic fluid utilizing apparatus
US3096074A (en) * 1960-12-06 1963-07-02 Rolls Royce Bladed rotors of machines such as gas turbines
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
WO2001071165A1 (de) 2000-03-23 2001-09-27 Alstom (Switzerland) Ltd Befestigung der beschaufelung einer strömungsmaschine
US20030143077A1 (en) * 2000-03-23 2003-07-31 Eduard Gotzfried Fastening of the blades of a compression machine
US6830435B2 (en) 2000-03-23 2004-12-14 Alstom Technology Ltd Fastening of the blades of a compression machine
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US6929453B2 (en) 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20080003098A1 (en) * 2004-12-21 2008-01-03 Alstom Technology Ltd. Method for modification of a turbocompressor
EP1707747A1 (de) * 2005-03-18 2006-10-04 Siemens Aktiengesellschaft Schaufelfussbefestigung und entsprechendes Montageverfahren
RU2296227C1 (ru) * 2005-08-18 2007-03-27 Открытое Акционерное Общество "Теплоэнергосервис-ЭК" (ОАО "Теплоэнергосервис-ЭК") Узел соединения лопаток с ротором турбомашины (варианты)
US20090110553A1 (en) * 2007-10-30 2009-04-30 Min-I Wu Omnidirectional electric fan and fan blade structure

Also Published As

Publication number Publication date
BE760151A (fr) 1971-06-10
NL7000530A (enrdf_load_html_response) 1971-06-15
GB1296791A (enrdf_load_html_response) 1972-11-15
DE1963922C3 (de) 1973-01-04
DE1963922A1 (de) 1971-06-24
DE1963922B2 (de) 1972-06-22
CH516731A (de) 1971-12-15
FR2072221A5 (enrdf_load_html_response) 1971-09-24

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Legal Events

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AS Assignment

Owner name: SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND, SWIT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR;REEL/FRAME:005221/0890

Effective date: 19890530