US3851994A - Blading for axial flow turbo-machine - Google Patents

Blading for axial flow turbo-machine Download PDF

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Publication number
US3851994A
US3851994A US00323094A US32309473A US3851994A US 3851994 A US3851994 A US 3851994A US 00323094 A US00323094 A US 00323094A US 32309473 A US32309473 A US 32309473A US 3851994 A US3851994 A US 3851994A
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United States
Prior art keywords
blade
twist
axis
rotor
blading
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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
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US00323094A
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English (en)
Inventor
C Seippel
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.)
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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Application filed by BBC Brown Boveri France SA filed Critical BBC Brown Boveri France SA
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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form

Definitions

  • the object of this invention is to provide a twisted blade strurcture in which the amount of twist will remain the same, i.e., both at-standstill and during operation. This objective is attained by selecting the degree vision need be made for any potential changes in shape of the blade during operation. 7
  • FIG. I is aschematic presentation of a twisted blade illustrating the nature of the centrifugal forces acting upon it under dynamic conditions
  • FIG. 2 is a view similar to FIG. 1 but wherein the blade is straight; i.e., non-twistedi I
  • FIG. 3 illustrates a blade of the twist type when at rest, i.e., under static conditions;
  • FIG. 4 illustrates a twisted blade constructed in accordance with the principles of this invention.
  • the tip 1 which represents a thinsection of a turbine blade having an airfoil profile.
  • the leading and trailing edges of the blade are designated by 2 and 3, respectively.
  • the tip 1 is secured to pin 5 which is located vertically to the axis of rotation 6, and thus in a radial direction.
  • Centrifugal forces acting upon the masses in the center of the mass exert a pull in the axial direction of the pin and are designated by vector 4-7.
  • the centrifugal forces which originate from the masses at point 2 are depicted by a radial vector 2-8 which intersects the axis 'of rotation 6 vertically. Since point 2 is staggered in the peripheral direction in relation to point 4, the forces 2-8 and 4-7 are not parallel.
  • Vector 2-8 can be resolved into two components, one such component 2-9 being parallel to vector 4-7, and the other component 9-8 perpendicular to the latter andfunctioning in a tangential direction.
  • the radial forces 3-10 can be resolved into two components, one such component 3-11 being parallel to vector 4-7 and the other component I1-l0perpendicular to the latter.
  • Those components which are 'parallel to the vector 4-7 will form a resultant which exerts a purely tensional force upon the pin 5 if, as stipulated, point 4 represents the center of mass for the tip 1. Under the same conditions will the perpendicular vector components exert a purely torsional force onto the pin 5.
  • FIG. 2 shows a rotor 12 upon which is fastened a circumferential array of blading.
  • the blade is not twisted about its longitudinal axis and it has a constant cross-sectional profile throughout its entire length.
  • the axis 14 of the center of mass is located radially to the axis of rotation 6.
  • FIG. 3 shows a blade which has a sharp twist
  • the blade being in the rest, i.e., when the .rotor is at standstill.
  • the forces generated on the turbine blade are not parallel to each other, and are not perpendicular, but rather are inclined to the axis of rotation 6.
  • the blades 16 tend to straighten out under the influence of the centrifugal forces, and to assume a position perpendicular to the axis of rotation, thus tending to untwist the blade, in known manner, in the direction of the arrows 17.
  • FIG. 4 illustrates an embodiment of a blade structured in accordance with the invention.
  • the blade made of metal, is connected to the rotor 12 along the path 19-20-21. It is designedin the form of a control wing where all of the force generating vectors 19-22, 20-23 and 21-24 are located in a radial direction, that is to say, they intersect the axis of rotation 6 at an angle of It will be readily apparent that such a blade structure can not and'will not change its shape by twisting or untwisting when subjected to centrifugal forces during rotation of the rotor.
  • the invention is not limited to the specific blade design illustrated in FIG. 4 but rather other configurations may be adopted by which the same result can be obtained.
  • the thickness or the length of the cord of the profile diminishes from within to without.
  • B is the angle between the principal inertia axis and the circumferential direction.
  • dB/dr is the degree of blade twist
  • T is the resultant torsion moment of the blade part from the distance r to the end of the blade P is the resultant tension force of this part of the blade A is the cross-sectional area of the profile
  • I 1 are the maximum and minimum moments of inertia of the blade profile
  • the shape of the blade can deviate somewhat in actual practice from the theoretical shape as defined by the above equation if a slight correction is indicated for purposes of flow-engineering.
  • dB/dr is the degree of blade twist
  • T is the resultant torsion moment of the blade part from the distance r to the end of the blade P is the resultant tension force of this part of the blade A is the cross-sectional area of the profile.
  • l 1 are the maximum and minimum moments of inertia of the blade profile thereby maintaining constant the amount of the blade twist under the influence of centrifugal forces acting thereon when the motor is operating.
  • Turbine blading as defined in claim 1 wherein all centrifugal force generating vectors along the surface of the blade between its leading and trailing edges extend in a radial direction from the axis of rotation of the rotor.
US00323094A 1972-01-20 1973-01-12 Blading for axial flow turbo-machine Expired - Lifetime US3851994A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH76772A CH541065A (de) 1972-01-20 1972-01-20 Verdrillte Laufschaufel einer axial durchströmten Turbomaschine

Publications (1)

Publication Number Publication Date
US3851994A true US3851994A (en) 1974-12-03

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ID=4194695

Family Applications (1)

Application Number Title Priority Date Filing Date
US00323094A Expired - Lifetime US3851994A (en) 1972-01-20 1973-01-12 Blading for axial flow turbo-machine

Country Status (3)

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US (1) US3851994A (ja)
CH (1) CH541065A (ja)
FR (1) FR2168797A5 (ja)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4120609A (en) * 1976-06-14 1978-10-17 Wallace Murray Corporation Sheet metal fan
US4284388A (en) * 1975-11-03 1981-08-18 Polska Akademia Nauk, Instytut Maszyn Przeplywowych Moving blade for thermic axial turbomachines
US4585395A (en) * 1983-12-12 1986-04-29 General Electric Company Gas turbine engine blade
US4682935A (en) * 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
US5044885A (en) * 1989-03-01 1991-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Mobile blade for gas turbine engines providing compensation for bending moments
US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
US6338609B1 (en) * 2000-02-18 2002-01-15 General Electric Company Convex compressor casing
EP1331360A2 (en) * 2002-01-18 2003-07-30 ALSTOM (Switzerland) Ltd Arrangement of vane and blade aerofoils in a turbine exhaust section
WO2009126996A1 (en) * 2008-04-14 2009-10-22 Atlantis Resources Corporation Pte Limited Blade for a water turbine
US20110210548A1 (en) * 2007-11-23 2011-09-01 Conrad Sevenster Control system for extracting power from water flow
US8633609B2 (en) 2008-04-14 2014-01-21 Atlantis Resources Corporation Pte Limited Sub sea central axis turbine with rearwardly raked blades
US8664790B2 (en) 2009-04-28 2014-03-04 Atlantis Resources Corporation Pte Limited Underwater power generator with dual blade sets
US8920200B2 (en) 2009-10-27 2014-12-30 Atlantis Resources Corporation Pte Connector for mounting an underwater power generator
US20150337664A1 (en) * 2012-12-13 2015-11-26 Nuovo Pignone Srl Turbomachine blade, corresponding turbomachine and method of manufacturing a turbine blade
US9568009B2 (en) 2013-03-11 2017-02-14 Rolls-Royce Corporation Gas turbine engine flow path geometry

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993015321A1 (en) * 1992-01-23 1993-08-05 Tovarischestvo S Ogranichennoi Otvetstvennostju 'varion' Axial fan
RU2450166C1 (ru) * 2010-08-30 2012-05-10 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Осевой вентилятор

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB131648A (ja) *
US2116055A (en) * 1936-01-17 1938-05-03 Weichwald John Propeller
GB614074A (en) * 1946-07-02 1948-12-09 Aubrey Lawrence Collins Improvements in or relating to fans
FR1187872A (fr) * 1957-10-18 1959-09-17 Pale pour voilure tournante
US2928653A (en) * 1955-12-22 1960-03-15 Gen Electric Variable angle blade for fluid flow machines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB131648A (ja) *
US2116055A (en) * 1936-01-17 1938-05-03 Weichwald John Propeller
GB614074A (en) * 1946-07-02 1948-12-09 Aubrey Lawrence Collins Improvements in or relating to fans
US2928653A (en) * 1955-12-22 1960-03-15 Gen Electric Variable angle blade for fluid flow machines
FR1187872A (fr) * 1957-10-18 1959-09-17 Pale pour voilure tournante

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4284388A (en) * 1975-11-03 1981-08-18 Polska Akademia Nauk, Instytut Maszyn Przeplywowych Moving blade for thermic axial turbomachines
US4120609A (en) * 1976-06-14 1978-10-17 Wallace Murray Corporation Sheet metal fan
US4585395A (en) * 1983-12-12 1986-04-29 General Electric Company Gas turbine engine blade
US4682935A (en) * 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
US5044885A (en) * 1989-03-01 1991-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Mobile blade for gas turbine engines providing compensation for bending moments
US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
US6338609B1 (en) * 2000-02-18 2002-01-15 General Electric Company Convex compressor casing
EP1331360A2 (en) * 2002-01-18 2003-07-30 ALSTOM (Switzerland) Ltd Arrangement of vane and blade aerofoils in a turbine exhaust section
EP1331360A3 (en) * 2002-01-18 2004-08-18 ALSTOM (Switzerland) Ltd Arrangement of vane and blade aerofoils in a turbine exhaust section
US20110210548A1 (en) * 2007-11-23 2011-09-01 Conrad Sevenster Control system for extracting power from water flow
CN102066744A (zh) * 2008-04-14 2011-05-18 亚特兰蒂斯能源有限公司 水力涡轮机叶片
US20110176915A1 (en) * 2008-04-14 2011-07-21 Atlantis Resources Corporation Pte Ltd. Blade for a water turbine
WO2009126996A1 (en) * 2008-04-14 2009-10-22 Atlantis Resources Corporation Pte Limited Blade for a water turbine
US8633609B2 (en) 2008-04-14 2014-01-21 Atlantis Resources Corporation Pte Limited Sub sea central axis turbine with rearwardly raked blades
CN102066744B (zh) * 2008-04-14 2014-07-23 亚特兰蒂斯能源有限公司 海底涡轮机叶片
US8801386B2 (en) 2008-04-14 2014-08-12 Atlantis Resources Corporation Pte Limited Blade for a water turbine
US8664790B2 (en) 2009-04-28 2014-03-04 Atlantis Resources Corporation Pte Limited Underwater power generator with dual blade sets
US8920200B2 (en) 2009-10-27 2014-12-30 Atlantis Resources Corporation Pte Connector for mounting an underwater power generator
US20150337664A1 (en) * 2012-12-13 2015-11-26 Nuovo Pignone Srl Turbomachine blade, corresponding turbomachine and method of manufacturing a turbine blade
US9568009B2 (en) 2013-03-11 2017-02-14 Rolls-Royce Corporation Gas turbine engine flow path geometry

Also Published As

Publication number Publication date
FR2168797A5 (ja) 1973-08-31
CH541065A (de) 1973-08-31

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