US1749528A - Blading for reaction turbines - Google Patents

Blading for reaction turbines Download PDF

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Publication number
US1749528A
US1749528A US108728A US10872826A US1749528A US 1749528 A US1749528 A US 1749528A US 108728 A US108728 A US 108728A US 10872826 A US10872826 A US 10872826A US 1749528 A US1749528 A US 1749528A
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US
United States
Prior art keywords
blading
steam
blades
passage
line
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
US108728A
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English (en)
Inventor
Freudenreich Jean De
Frey Karl
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 Germany
BBC Brown Boveri France SA
Original Assignee
BBC Brown Boveri France SA
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 BBC Brown Boveri France SA filed Critical BBC Brown Boveri France SA
Priority claimed from DEA48063D external-priority patent/DE566764C/de
Application granted granted Critical
Publication of US1749528A publication Critical patent/US1749528A/en
Anticipated expiration legal-status Critical
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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics

Definitions

  • SWITZERLAND A JOINT-STOCK COMPANY OF SWITZERLAND.
  • This invention relates to the construction of turbines actuated by expansion fluid, as ex-' amplified by steam turbines. It pertains particularly to steam turbines of the reaction type, and has to do with the construction or arrangement of theblading for both or either the stator or rotor;
  • the general object of the invention is the provision of a blading arrangement for reaction turbines which will increase the power efliciency of the engine.
  • Another object is the provision of a blading arrangement which will, in many instances, permita reduction in the size of the machines.
  • Another object is the provision of a construction which will reduce cost, by decreasing the number ofblades in a stage.
  • Fig. 1 is a diagrammatic illustration of a portion of a stage of blading demonstrative ot the invention, showing three blades each of adjacent stator and rotor rings, the blades being shown in section taken concentrically I with the turbine axis.
  • Fig. 2 is a graph illustrating the relationship of parts of the blade profile.
  • Fig. 3 is a section diagram of blading of the conventional Parsons design.
  • Fig. 4 is a diagram of a blading profile demonstrative of the invention in a. design differing from that of Fig. 1. v
  • Fig. 5 is a graph illustrating the relationship of certain parts of the respective struc- Heretofore in thedesigning oi reaction turbines, so far as we have been able to ascertam,rap1d changes 1n the cross section and r
  • the movin blades are desi 108,728, and in Switzerland May 27, 1925.
  • Fig. 1 illustrates a profile and arrangement of our improved blading, as applied to an axial-flow steam turbine.
  • the upper row of blades, designated 10, repre sents-a section of blading on a wheel or rotor of a reaction turbine, while the row designated 11 represents a section of 'a portion of the adjacent row offixed blading.
  • our new blading construction is equally ada ted for both moving and stationa stages 0 reaction turbines, and that it can e employed to best advantage when utilized in both in conjunction.
  • the pressure por-' tion may be regarded as the zone X, the intermediate portion as the zone Y and the velocity portion as the zone Z.
  • the change in direction of the flow passage is relatively abrupt as compared with the previous design, resulting in the turning of the steam path to an acute exit angle in considerably shorter length.
  • the exit angle 1s approximately 18, which is suggested as re resenting an average between the limits of t e most efiective arrangements,
  • the line a in Fig. 2 represent the development of the median steam path a.w between the blades, and the cross sections 0, 1, 2, 3 .7,- set np on the line a represent the radii of the correspondingly numbered circles inscribed in the steam passage tangent
  • the line (Z generated along the ends of the radii 0 should incline toward the line a at an angle of something over 15 throughout that portion representative of the intermediate zone Y.
  • the end portions of the line d will deviate from the intermediate portion, the part Z representing the comparatively straight restricted velocity portion of the steam passage, while the part f represents the portions where the blades are rounded ed at entry in the example shown.
  • portion Z represents only between one fourth to one fifth of the length of the entire path wa.
  • An effective design may also generate a line corresponding to the line d but curved, thechord of the intermediate portion being inclined at an angle of more than 15 to the line a.
  • said curved line in the intermediate portion should be convex upwardly. If concave, it is a sign that the transition will be gradual.
  • the dotted curved in Fig. 2 is illustrative of one form.
  • Fig. 3 is shown a diagram of standard Parsons blading
  • Fig. 5 a diagrammatic analysis of the same obtained by the method described above. It will be observed that in this diagram the line 03, corresponding to the line d of Fig. 2', is concave upwardly in the intermediate portion and makes an angle of less than15 to the line a; The narrowest section Z comprises a considerably greater proportion of the line d, demonstrating that the length of the contracted exit portion of the steam channel is considerably greater than is the case with profiles arranged according to the present invention.
  • Fig. 4 is shown an example of such an arrangement, the profile being shaped in accordance with the method described above, and illustrated by the line d in Fig. 5. As demonstrated by the analysis, this design presents a profile'frpm which the line (1'' is generated to extend through the greater proportion of its length at an angle of more than 15 to the line a".
  • Reaction turbine blading comprising blades extending radially and defining intervening steam passages,the blades having a profile and arrangement giving said passages a relatively wide pressure portion at the enshort and ree exit side, said an intermediate portion of rapidly contracting width s'tricted velocity portion at t wherein the blade profile converges on the mean steam path of the passage at a rate elxceeding that of-the sides of an angle of 2.
  • Reaction turbine bladin as specified in claim 1, wherein the intermediate portion of the steam passa e changes the direction of steam flow rapitfi 3.
  • Reaction turliine blading as specified in claim 1, wherein the pressure portion of the steam assage is longer, on the axial line of the tur ine, than is the velocity portion.
  • Reaction turbine blading as specified in glaim '1, wherein the exit angle is less than 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US108728A 1925-05-27 1926-05-13 Blading for reaction turbines Expired - Lifetime US1749528A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH115781T 1925-05-27
DEA48063D DE566764C (de) 1926-06-22 1926-06-22 UEberdruckbeschaufelung fuer Dampf- und Gasturbinen

Publications (1)

Publication Number Publication Date
US1749528A true US1749528A (en) 1930-03-04

Family

ID=31947297

Family Applications (2)

Application Number Title Priority Date Filing Date
US108728A Expired - Lifetime US1749528A (en) 1925-05-27 1926-05-13 Blading for reaction turbines
US206491A Expired - Lifetime US1673554A (en) 1925-05-27 1927-07-18 Blading for reaction turbines

Family Applications After (1)

Application Number Title Priority Date Filing Date
US206491A Expired - Lifetime US1673554A (en) 1925-05-27 1927-07-18 Blading for reaction turbines

Country Status (6)

Country Link
US (2) US1749528A (de)
BE (1) BE334235A (de)
CH (2) CH115781A (de)
DE (1) DE522464C (de)
FR (2) FR616250A (de)
GB (2) GB252702A (de)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3140042A (en) * 1961-08-15 1964-07-07 Fujii Noriyoshi Wheels for centrifugal fans of the forward curved multiblade type
US3314647A (en) * 1964-12-16 1967-04-18 Vladimir H Pavlecka High energy conversion turbines
US4002414A (en) * 1971-10-21 1977-01-11 Coleman Jr Richard R Compressor-expander rotor as employed with an integral turbo-compressor wave engine
US4165950A (en) * 1976-09-06 1979-08-28 Hitachi, Ltd. Fan having forward-curved blades
US4624105A (en) * 1982-03-09 1986-11-25 Honda Giken Kogyo Kabushiki Kaisha Hydraulic torque converter
US4626174A (en) * 1979-03-16 1986-12-02 Hitachi, Ltd. Turbine blade
US4778335A (en) * 1984-09-18 1988-10-18 Fuji Electric Co., Ltd. Total flow turbine stage
US4809498A (en) * 1987-07-06 1989-03-07 General Electric Company Gas turbine engine
EP1223307A2 (de) * 2001-01-12 2002-07-17 Mitsubishi Heavy Industries, Ltd. Gasturbinenschaufelform
US6705834B1 (en) * 1999-12-16 2004-03-16 Atlas Copco Tools Ab Axial flow turbine type rotor machine for elastic fluid operation
US20050019157A1 (en) * 2001-08-31 2005-01-27 Junichi Tominaga Axial flow turbine
US20130064670A1 (en) * 2007-02-28 2013-03-14 Nobuaki Kizuka Turbine blade
US20170204728A1 (en) * 2014-06-26 2017-07-20 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade row, turbine stage, and axial-flow turbine
US20180030835A1 (en) * 2015-02-10 2018-02-01 Mitsubishi Hitachi Power Systems, Ltd. Turbine and gas turbine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL300321A (de) * 1962-11-30
JPS5614802A (en) * 1979-07-18 1981-02-13 Hitachi Ltd Profile of accelerating blade
DE3201436C1 (de) * 1982-01-19 1983-04-21 Kraftwerk Union AG, 4330 Mülheim Turbomaschinenschaufel
DE3202855C1 (de) * 1982-01-29 1983-03-31 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Verminderung von Sekundaerstroemungsverlusten in einem beschaufelten Stroemungskanal
US4900230A (en) * 1989-04-27 1990-02-13 Westinghouse Electric Corp. Low pressure end blade for a low pressure steam turbine
JP3188128B2 (ja) * 1995-02-21 2001-07-16 株式会社豊田中央研究所 車輌用トルクコンバータのステータ
WO1998019048A1 (en) * 1996-10-28 1998-05-07 Siemens Westinghouse Power Corporation Airfoil for a turbomachine

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3140042A (en) * 1961-08-15 1964-07-07 Fujii Noriyoshi Wheels for centrifugal fans of the forward curved multiblade type
US3314647A (en) * 1964-12-16 1967-04-18 Vladimir H Pavlecka High energy conversion turbines
US4002414A (en) * 1971-10-21 1977-01-11 Coleman Jr Richard R Compressor-expander rotor as employed with an integral turbo-compressor wave engine
US4165950A (en) * 1976-09-06 1979-08-28 Hitachi, Ltd. Fan having forward-curved blades
US4626174A (en) * 1979-03-16 1986-12-02 Hitachi, Ltd. Turbine blade
US4624105A (en) * 1982-03-09 1986-11-25 Honda Giken Kogyo Kabushiki Kaisha Hydraulic torque converter
US4778335A (en) * 1984-09-18 1988-10-18 Fuji Electric Co., Ltd. Total flow turbine stage
US4809498A (en) * 1987-07-06 1989-03-07 General Electric Company Gas turbine engine
US6705834B1 (en) * 1999-12-16 2004-03-16 Atlas Copco Tools Ab Axial flow turbine type rotor machine for elastic fluid operation
EP1223307A2 (de) * 2001-01-12 2002-07-17 Mitsubishi Heavy Industries, Ltd. Gasturbinenschaufelform
EP1223307A3 (de) * 2001-01-12 2004-03-10 Mitsubishi Heavy Industries, Ltd. Gasturbinenschaufelform
US6799948B2 (en) * 2001-01-12 2004-10-05 Mitsubishi Heavy Industries, Ltd. Blade of a gas turbine
US20050019157A1 (en) * 2001-08-31 2005-01-27 Junichi Tominaga Axial flow turbine
US7048509B2 (en) * 2001-08-31 2006-05-23 Kabushiki Kaisha Toshiba Axial flow turbine
US20130064670A1 (en) * 2007-02-28 2013-03-14 Nobuaki Kizuka Turbine blade
US20170204728A1 (en) * 2014-06-26 2017-07-20 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade row, turbine stage, and axial-flow turbine
US11220909B2 (en) * 2014-06-26 2022-01-11 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade row, turbine stage, and axial-flow turbine
US20180030835A1 (en) * 2015-02-10 2018-02-01 Mitsubishi Hitachi Power Systems, Ltd. Turbine and gas turbine
US10655471B2 (en) * 2015-02-10 2020-05-19 Mitsubishi Hitachi Power Systems, Ltd. Turbine and gas turbine

Also Published As

Publication number Publication date
US1673554A (en) 1928-06-12
BE334235A (de) 1926-05-21
FR616250A (fr) 1927-01-29
GB252702A (en) 1927-08-15
GB272837A (en) 1927-12-08
DE522464C (de) 1931-04-09
CH115781A (de) 1926-07-16
CH122943A (de) 1927-10-17
FR32194E (fr) 1927-09-12

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