US3756019A - Gas turbine blade arrangement - Google Patents

Gas turbine blade arrangement Download PDF

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Publication number
US3756019A
US3756019A US00159449A US3756019DA US3756019A US 3756019 A US3756019 A US 3756019A US 00159449 A US00159449 A US 00159449A US 3756019D A US3756019D A US 3756019DA US 3756019 A US3756019 A US 3756019A
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United States
Prior art keywords
wheels
blades
turbine blades
turbine
extending
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
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US00159449A
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English (en)
Inventor
H Holzapfel
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Individual
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Individual
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • a gas turbine is formed with a first and a second stage, the first stage contains wheels on which turbine blades are concentrically arranged around compressor blades and the second stage contains wheels on which turbine blades are concentrically arranged around webs.
  • a combustion chamber is arranged to receive air after it has been compressed by the compressor blades in the first stage and has been guided but not further compressed by the webs in the second stage.
  • the compressed air After the compressed air is heated in the combustion chamber it passes over the turbine blades in the second stage and then over the turbine blades in the first stage.
  • the turbine blades in the first stage are hollow and air is withdrawn from the compressor side in the first stage and passed into the interior of the turbine blades to cool them.
  • the present invention is directed to a blade arrangement for use in a gas turbine and, more particularly, it concerns a multi-stage gas turbine in which the wheels of one stage contain both turbine blades and compressor blades while the wheels of another stage contain only turbine blades and webs for guiding air after it has been compressed by the compressor blades on the other wheels.
  • Gas turbines if they are of the multi-stage type, have the advantage that they provide a simple construction. However, if the compressor and turbine parts of gas turbines are separately arranged then a number of shafts corresponding to the number of stages involved are required and these shafts either concentrically surround each other or are arranged independently from one another. Such arrangements of the shafts are disadvantageous and are eliminated in gas turbines of the type which embody the present invention. Further, gas turbines which embody the present invention can be build in a compact, space saving manner.
  • the gas exiting from the turbine blades in the lower pressure or first stage of the turbine has a higher pressure than the gas entering the compressor blades at the same location. Accordingly, the hot gas flows from the turbine blade side toward the compressor blade side through sealing elements and as a result a decrease in pressure conditions takes place due to the heating of the air or gas entering the compressor blades.
  • German Pat. No. 819,758 a construction is illustrated in which the air supplied into the compressor blades is previously compressed.
  • a rotating sleeve is connected with the wheels of the turbine, the sleeve being provided with exterior vanes.
  • the vanes on the sleeve communicate with the compressor blades on the wheel through a flow channel.
  • the medium being used in the gas turbine after the medium being used in the gas turbine is compressed, it flows through wheels mounted on an output shaft and the wheels contain a circumferentially extending row of turbine blades secured radially outwardly from webs which connect the turbine blades to the output shaft.
  • the wheels connected to the output shaft are used only for performing useful work.
  • wheels similarly arranged are required to effect a compressing action on the gas passing through the turbine, however, in the present arrangement no such additional work is required.
  • the webs located inwardly from the turbine blades on the wheels are used merely for guiding the compressed air and do not provide any additional compressing action.
  • the compressed air or gas after leaving the wheels has a higher temperature due to its passage through the combustion chamber but it has a lower pressure as compared to the pressure developed in the gas by the compressor blades in the prior art wheels.
  • the turbine blades in the wheels on the output shaft are configured so that the pressure at the inlet to the compressor blades on the preceding stage is the same as the pressure of the air or gas exiting from the turbine blades on the preceding stage.
  • Another characteristic feature of the invention relates to the manner in which the turbine blades can be cooled.
  • the turbine blades are hollow and extend radially outwardly from a annular shaped base member which separates the turbine blades from the radially inwardly arranged compressor blades.
  • the annular base member has a plurality of bores connecting the compressor side of the annular base member with the interior of the turbine blades.
  • FIG. I a gas turbine is shown having runners or wheels ll mounted on a stationary shaft 2 in a counterrotating manner with the shaft being secured to a casing, not shown.
  • Each of the wheels ll consists of a circumferentially extending row of radially extending compressor vanes 3 located radially inwardly from a circumferentially extending row of radially extending turbine blades 4.
  • An annular shaped base member 5 is secured to the base of the turbine blades 4 and to the tips or radially outer ends of the compressor blades 3.
  • second wheels 6 affixed to a driven or output shaft 7 which is aligned with the stationary shaft 1.
  • the second wheels though, provided with radially outer circumferentially extending row of turbine blades 8, do not have the radially inner row of compressor blades of wheels 1.
  • the turbine blades 8 are connected to the output shaft 7 by means or radially extending webs 9.
  • the webs 9 serve as guides for the compressed air after its passage through the compressor blades 3 on wheels 1 and the webs do not perform any additional compressing action on the air.
  • a combustion chamber 10 Downstream from the second wheels 6, a combustion chamber 10 is arranged to receive the air after its passage through the compressor blades 3 and the webs 9 and after it is heated, the air is directed through the turbine blades 8 on the second wheels 6 and then through the turbine blades 4 on the wheels 1.
  • the air flows from an inlet 11 into the compressor blades on the wheels 1 and is compressed as it passes through the various wheels in the first stage of the turbine. After passing through the compressor blades, the compressed air is guided by the webs 9 on the second wheels 6 into the combustion chamber 10 where an increase in temperature is imparted to the air.
  • the heated air or gas flows through the radially outer portion of the second wheels passing through the turbine blades 8 and a portion of its energy is converted into useful work through the output shaft 7.
  • the turbine blades 4 are hollow and the base member 5 supporting the turbine blades is provided with bores 13, not FIGS. 2 and 3.
  • the bores extend from the compressor side of the base member into he interior of the turbine blades. Due to the arrangement of the bores 13, a small flow of the air being compressed enters into the interior of the turbine blades for producing a cooling effect.
  • a gas turbine comprising a stationary shaft, a plurality of first wheels mounted on said stationary shaft, each of said wheels comprising a circumferentially extending row of radially extending compressor blades and a circumferentially extending row of turbine blades concentrically disposed about and extendinG radially outwardly from the radially outer ends of said compressor blades, a combustion chamber arranged to receive air compressed in said compressor blades on said first wheels for heatinG the air and returning it for flow over said turbine blades on said first wheels, a driven output shaft extending axially from said stationary shaft and located between said stationary shaft and on said output shaft, wherein the improvement comprises that: said second wheels on said drive shaft comprise a circumferentially arranged row of radially outwardly extending webs and a circumferentially arranged row of radially outwardly extending turbine blades concentrically disposed about and extending radially outwardly from said row of webs, said webs arranged to receive the compressed air from said compressor blades on said
  • a gas turbine as set forth in claim 1, characterized in that turbine blades on said first wheels being hollow, an annular base member extending circumferentially around the radially inner ends of said turbine blades and the radially outer ends of said compressor blades of said first wheels and separating said turbine blades from said compressor blades, and said base member having bores extending therethrough from said compressor blade side to said turbine blade side with the bores communicating with the hollow interiors of said turbine blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
US00159449A 1970-07-03 1971-07-02 Gas turbine blade arrangement Expired - Lifetime US3756019A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2032964A DE2032964C3 (de) 1970-07-03 1970-07-03 Gasturbinenanlage mit gegenläufigen Laufrädern

Publications (1)

Publication Number Publication Date
US3756019A true US3756019A (en) 1973-09-04

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ID=5775690

Family Applications (1)

Application Number Title Priority Date Filing Date
US00159449A Expired - Lifetime US3756019A (en) 1970-07-03 1971-07-02 Gas turbine blade arrangement

Country Status (4)

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US (1) US3756019A (enExample)
DE (1) DE2032964C3 (enExample)
FR (1) FR2097170B1 (enExample)
GB (1) GB1353400A (enExample)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301649A (en) * 1979-08-24 1981-11-24 General Motors Corporation Single rotor engine with turbine exhausting to subatmospheric pressure
US4693075A (en) * 1984-10-31 1987-09-15 Andrew Sabatiuk Gas turbine engines employing fixed volume combustion
US4757682A (en) * 1985-05-20 1988-07-19 Eugene Bahniuk Axial flow turbine
US4843814A (en) * 1985-12-02 1989-07-04 Von Ingelheim Peter G Assembly for producing a propulsive force
US5224339A (en) * 1990-12-19 1993-07-06 Allied-Signal Inc. Counterflow single rotor turbojet and method
RU2306424C1 (ru) * 2006-03-17 2007-09-20 Закрытое акционерное общество "ЭНТЭК" Проточная часть паровой турбины
US20110146228A1 (en) * 2009-12-21 2011-06-23 John Lewis Baughman Power extraction system
US20110146289A1 (en) * 2009-12-21 2011-06-23 John Lewis Baughman Power extraction method
US20120110976A1 (en) * 2010-11-08 2012-05-10 Marius Angelo Paul Universal aero space , naval eternal technology systems
US8192141B1 (en) * 2007-04-05 2012-06-05 The United States Of America As Represented By The Secretary Of The Air Force Dual compression rotor
CN102575583A (zh) * 2009-10-14 2012-07-11 涡轮梅坎公司 用于过滤内燃引擎进口空气的具有通风结构的装置
US20220333611A1 (en) * 2021-04-14 2022-10-20 Stokes Technology Development Ltd. Counter-rotating axial air moving device

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3004980C2 (de) * 1980-02-11 1984-10-11 Rudolf E. New York N.Y. Fengler Propeller-Überschall-Strahltriebwerk für Flugzeuge und Flugkörper
BG99154A (en) * 1994-11-01 1996-06-28 Givechev Gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE735392C (de) * 1941-06-26 1943-05-13 Aeg Einrichtung zur Kuehlung von Gasturbinenschaufeln
DE892046C (de) * 1953-08-20 Maschinenfabrik Augsburg-Nürnlberg A. G., Augsburg Leitapparat für axial durchströmte Kreiselradmaschinen
US2702985A (en) * 1944-01-31 1955-03-01 Power Jets Res & Dev Ltd Gas turbine power plant with power take-off from rotatable guide blading
DE1085718B (de) * 1958-11-26 1960-07-21 Daimler Benz Ag Gasturbinentriebwerk
US3391540A (en) * 1965-08-05 1968-07-09 Snecma Turbojet engines having contrarotating compressors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE892046C (de) * 1953-08-20 Maschinenfabrik Augsburg-Nürnlberg A. G., Augsburg Leitapparat für axial durchströmte Kreiselradmaschinen
DE735392C (de) * 1941-06-26 1943-05-13 Aeg Einrichtung zur Kuehlung von Gasturbinenschaufeln
US2702985A (en) * 1944-01-31 1955-03-01 Power Jets Res & Dev Ltd Gas turbine power plant with power take-off from rotatable guide blading
DE1085718B (de) * 1958-11-26 1960-07-21 Daimler Benz Ag Gasturbinentriebwerk
US3391540A (en) * 1965-08-05 1968-07-09 Snecma Turbojet engines having contrarotating compressors

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301649A (en) * 1979-08-24 1981-11-24 General Motors Corporation Single rotor engine with turbine exhausting to subatmospheric pressure
US4693075A (en) * 1984-10-31 1987-09-15 Andrew Sabatiuk Gas turbine engines employing fixed volume combustion
US4757682A (en) * 1985-05-20 1988-07-19 Eugene Bahniuk Axial flow turbine
US4843814A (en) * 1985-12-02 1989-07-04 Von Ingelheim Peter G Assembly for producing a propulsive force
US5224339A (en) * 1990-12-19 1993-07-06 Allied-Signal Inc. Counterflow single rotor turbojet and method
RU2306424C1 (ru) * 2006-03-17 2007-09-20 Закрытое акционерное общество "ЭНТЭК" Проточная часть паровой турбины
US8192141B1 (en) * 2007-04-05 2012-06-05 The United States Of America As Represented By The Secretary Of The Air Force Dual compression rotor
US8726635B1 (en) * 2007-04-05 2014-05-20 The United States Of America As Represented By The Secretary Of The Air Force Gas turbine engine with dual compression rotor
US8356469B1 (en) 2007-04-05 2013-01-22 The United States Of America As Represented By The Secretary Of The Air Force Gas turbine engine with dual compression rotor
US8685126B2 (en) 2009-10-14 2014-04-01 Turbomeca Device for filtering the intake air of an internal combustion engine having ventilation means
CN102575583A (zh) * 2009-10-14 2012-07-11 涡轮梅坎公司 用于过滤内燃引擎进口空气的具有通风结构的装置
CN102575583B (zh) * 2009-10-14 2015-04-01 涡轮梅坎公司 用于过滤内燃引擎进口空气的具有通风结构的装置
US20110146289A1 (en) * 2009-12-21 2011-06-23 John Lewis Baughman Power extraction method
US20110146228A1 (en) * 2009-12-21 2011-06-23 John Lewis Baughman Power extraction system
US20120110976A1 (en) * 2010-11-08 2012-05-10 Marius Angelo Paul Universal aero space , naval eternal technology systems
US20220333611A1 (en) * 2021-04-14 2022-10-20 Stokes Technology Development Ltd. Counter-rotating axial air moving device

Also Published As

Publication number Publication date
DE2032964A1 (de) 1972-01-05
FR2097170A1 (enExample) 1972-03-03
GB1353400A (en) 1974-05-15
FR2097170B1 (enExample) 1975-06-06
DE2032964B2 (de) 1973-09-20
DE2032964C3 (de) 1974-04-25

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