US3685921A - Gas turbine with variable blade distributor - Google Patents

Gas turbine with variable blade distributor Download PDF

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Publication number
US3685921A
US3685921A US61205A US3685921DA US3685921A US 3685921 A US3685921 A US 3685921A US 61205 A US61205 A US 61205A US 3685921D A US3685921D A US 3685921DA US 3685921 A US3685921 A US 3685921A
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US
United States
Prior art keywords
blade
blades
turbine
casing
guide ring
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
US61205A
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English (en)
Inventor
Lucien Dekeyser
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.)
Bennes Marrel SA
Original Assignee
Bennes Marrel 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 Bennes Marrel SA filed Critical Bennes Marrel SA
Application granted granted Critical
Publication of US3685921A publication Critical patent/US3685921A/en
Anticipated expiration legal-status Critical
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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

  • SHEET 2 [IF 4 GAS TURBINE WITH VARIABLE BLADE DISTRIBUTOR This invention relates to a gas turbine.
  • the object of the present invention is to achieve these results by producing an improved gas turbine specially adapted for driving a lorry or a motor vehicle.
  • a gas turbine comprising an annular guide ring located between a high pressure turbine rotor of a primary shaft and a low pressure turbine rotor of secondary shaft, the guide ring having pivotal blades arranged radially around the central axis of the turbine, each blade being mounted on a shaft provided with a pinion meshing with a gear ring coaxial to the general axis of the turbine, rotation of the gear ring being controlled by driving means.
  • These driving means preferably comprises a doubleacting jack which is connected by a connecting-rod to a bracket on the gear ring.
  • This jack may advantageously be constituted by a piston movable in a cylinder, in one direction, under the thrust of a compressed fluid and in the opposite direction, under the action of a spring, the pressure of the fluid for controlling the jack being variable by a regulator.
  • This regulator can be controlled either manually, or automatically, or by a combination of both.
  • FIG. 1 is a sectional view on the line I I of FIG. 2 of a gas turbine according to the invention
  • FIG. 2 is a section on the line H II of FIG. 1;
  • FIGS. 3 and 4 are detail views of parts of FIG. 2;
  • FIG. 5 is a diagrammatic section on the line V V of FIG. 2;
  • FIG. 6 is a developed view showing the orientation of the movable blades of the guide ring during the starting phase of the turbine;
  • FIG. 7 is a similar view to FIG. 6 corresponding to conditions of maximum power.
  • FIG. 8 illustrates the operation as an engine brake.
  • This turbine comprises a centrifugal compressor 1 and a high pressure bladed rotor 2 keyed on the same shaft 3, and a low pressure bladed rotor 4 which constitutes the power wheel which drives the output driving shaft 5 through the intermediary of a reduction gear 6.
  • the shaft 3 drives the elements of a gear box 7.
  • the admission of atmospheric air takes place through lateral intakes 8 while the exhaust gases are returned to atmosphere through two inlets 9 directed towards the rear of the turbine.
  • This guide ring comprises, immediately behind the high pressure rotor 2, arms 14 which support an internal annular element 55 for ensuring the continuity of the air jet. Behind these arms 14, is provided a group of movable blades 16. Thus, gases leaving the high pressure rotor 2 pass between the arms 14, then traverse the blades 16 before driving the power rotor 4.
  • the blades 16 are distributed radially about the general axis of the turbine. They are all identical and equidistant. For example, there may be eighteen blades 16, although it is to be understood that this number is given purely as an example.
  • each blade 16 is integral with a journal 17 surmounted by a shaft 18. On the free end of this shaft 18 there is keyed a toothed pinion 19.
  • each blade 16 are machined to a spherical profile in order to ensure, either contact, or minimum play, with the stationary parts which surround them, namely an internal, annular casing 22 and an external, annular casing 23. Thus, airtightness is ensured, whatever the angular position of the blades 16 and their journals 17.
  • Each journal 17 rotates in a fixed, bearing 24, and a ring 25 constitutes another bearing in which each shaft 18 rotates.
  • the rings 24 and 25 are housed inside a fixed column 26.
  • This contact between surfaces 20, 22 at the base of each blade assists in retaining the blade in position and avoidance of vibrations.
  • the pinions 19 preferably have conical toothing and they all mesh with a toothed wheel rim 33 which surrounds the guide rings 16. The guidance of this toothed rim 33 is ensured by two ball-races or rollerraces. 34
  • the rim 33 comprises a lateral bracket 36 FIG. on which there is pivoted by a shaft 37 one of the ends of a coupling rod 38. At its opposite end, this rod is connected by a pivot 39 to the piston rod 40 of a jack.
  • This jack comprises a piston 41 integral with the rod 40, which piston slides inside a fixed cylinder 42. Between the end wall 43 of the cylinder 42 and the piston 41, there is housed a compression spring 44. On the other side of the piston, i.e. near the other end wall 45, there is defined a variable volume chamber 46 which receives by known means which are not shown,- the oil of the hydraulic circuit for regulating the'turbine.
  • each arm has a transverse profile 47 as shown in FIG. 3, each arm being hollow, i.e. over their entire length there are channels 48 through which cooling air can circulate.
  • a gas turbine of the type having a high pressure turbine rotor, a low pressure turbine rotor and an intermediate annular guide ring disposed coaxially in a casing
  • said guide ring includes a plurality of blades each of which is mounted for rotation about an individual radially extending axis by means of a common gear ring disposed in meshing engagement with a pinion coaxially secured to each blade with each blade bearing on an inner spherical surface of said casing
  • the improvement comprising a plurality of stepped shaft means each having a pinion and a blade secured to opposite ends thereof, a pair of spaced apart bearing rings supporting each of said shafts in said casing, means locating each outermost bearing ring against radially outward displacement and spring means disposed intermediate each of said outermost bearing rings and a stepped portion of each stepped shaft whereby each of said blades is biased radially inwardly against said spherical surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Support Of The Bearing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US61205A 1969-08-14 1970-08-05 Gas turbine with variable blade distributor Expired - Lifetime US3685921A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6928154A FR2055780A1 (nl) 1969-08-14 1969-08-14

Publications (1)

Publication Number Publication Date
US3685921A true US3685921A (en) 1972-08-22

Family

ID=9039087

Family Applications (1)

Application Number Title Priority Date Filing Date
US61205A Expired - Lifetime US3685921A (en) 1969-08-14 1970-08-05 Gas turbine with variable blade distributor

Country Status (12)

Country Link
US (1) US3685921A (nl)
AT (1) AT309913B (nl)
CA (1) CA940051A (nl)
CH (1) CH520267A (nl)
CS (1) CS149924B2 (nl)
DE (1) DE2039064C3 (nl)
ES (1) ES382608A1 (nl)
FR (1) FR2055780A1 (nl)
GB (1) GB1313938A (nl)
NL (1) NL7012074A (nl)
SE (1) SE360425B (nl)
ZA (1) ZA705605B (nl)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US4150915A (en) * 1976-12-23 1979-04-24 Caterpillar Tractor Co. Variable geometry turbine nozzle
US4231703A (en) * 1978-08-11 1980-11-04 Motoren- Und Turbinen-Union Muenchen Gmbh Variable guide vane arrangement and configuration for compressor of gas turbine devices
US4277221A (en) * 1976-04-22 1981-07-07 Dominion Engineering Works Limited Wicket gate bearing seal
EP1188903A1 (fr) * 2000-09-18 2002-03-20 Snecma Moteurs Veine d'écoulement usinée pour turbomachine
US6394766B1 (en) * 1999-11-01 2002-05-28 James G. Gill Fan with adjustable guide vanes
US6709231B2 (en) * 2001-05-11 2004-03-23 Fiatavio S.P.A. Stator of a variable-geometry axial turbine for aeronautical applications
US20070086886A1 (en) * 2003-12-05 2007-04-19 Giuseppe Sassanelli Variable nozzle for a gas turbine
CN100346060C (zh) * 2003-03-14 2007-10-31 曼·B及W柴油机公开股份有限公司 径流式透平的导向装置
US20110110765A1 (en) * 2009-11-11 2011-05-12 Loc Quang Duong Inlet guide vane drive system with spring preload on mechanical linkage

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2931766C2 (de) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Dichtungseinrichtung für die freien Schaufelenden eines Verstell-Leitapparates einer Gasturbine
FR2599785B1 (fr) * 1986-06-04 1990-10-12 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
GB2206381B (en) * 1987-06-30 1991-10-09 Rolls Royce Plc A variable stator vane arrangement for a compressor
DE4100224C2 (de) * 1991-01-07 1994-05-19 Daimler Benz Ag Halterung eines Diffusors einer Gasturbine in einem Turbinengehäuse
DE4213716A1 (de) * 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
DE102007021448B4 (de) * 2006-05-18 2012-06-28 Man Diesel & Turbo Se Leitapparat für einen Abgasturbolader einer mit Schweröl betriebenen Hubkolben-Brennkraftmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
GB878988A (en) * 1957-10-31 1961-10-04 Maschf Augsburg Nuernberg Ag Improvements in or relating to a turbine or compressor inlet nozzle assembly
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
US3574479A (en) * 1968-09-17 1971-04-13 Leyland Gas Turbines Ltd Turbine having variable-angle nozzle guide vanes

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
GB878988A (en) * 1957-10-31 1961-10-04 Maschf Augsburg Nuernberg Ag Improvements in or relating to a turbine or compressor inlet nozzle assembly
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
US3574479A (en) * 1968-09-17 1971-04-13 Leyland Gas Turbines Ltd Turbine having variable-angle nozzle guide vanes

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US4277221A (en) * 1976-04-22 1981-07-07 Dominion Engineering Works Limited Wicket gate bearing seal
US4150915A (en) * 1976-12-23 1979-04-24 Caterpillar Tractor Co. Variable geometry turbine nozzle
US4231703A (en) * 1978-08-11 1980-11-04 Motoren- Und Turbinen-Union Muenchen Gmbh Variable guide vane arrangement and configuration for compressor of gas turbine devices
US6394766B1 (en) * 1999-11-01 2002-05-28 James G. Gill Fan with adjustable guide vanes
FR2814205A1 (fr) * 2000-09-18 2002-03-22 Snecma Moteurs Turbomachine a veine d'ecoulement ameliore
EP1188903A1 (fr) * 2000-09-18 2002-03-20 Snecma Moteurs Veine d'écoulement usinée pour turbomachine
US6602049B2 (en) 2000-09-18 2003-08-05 Snecma Moteurs Compressor stator having a constant clearance
US6709231B2 (en) * 2001-05-11 2004-03-23 Fiatavio S.P.A. Stator of a variable-geometry axial turbine for aeronautical applications
CN100346060C (zh) * 2003-03-14 2007-10-31 曼·B及W柴油机公开股份有限公司 径流式透平的导向装置
US20070086886A1 (en) * 2003-12-05 2007-04-19 Giuseppe Sassanelli Variable nozzle for a gas turbine
US7354242B2 (en) * 2003-12-05 2008-04-08 Nuovo Pignone Holding S.P.A. Variable nozzle for a gas turbine
US20110110765A1 (en) * 2009-11-11 2011-05-12 Loc Quang Duong Inlet guide vane drive system with spring preload on mechanical linkage
US8534990B2 (en) * 2009-11-11 2013-09-17 Hamilton Sundstrand Corporation Inlet guide vane drive system with spring preload on mechanical linkage

Also Published As

Publication number Publication date
FR2055780A1 (nl) 1971-04-30
DE2039064C3 (de) 1974-05-09
SE360425B (nl) 1973-09-24
ES382608A1 (es) 1974-12-16
GB1313938A (en) 1973-04-18
CA940051A (en) 1974-01-15
AT309913B (de) 1973-09-10
CH520267A (fr) 1972-03-15
DE2039064A1 (de) 1971-09-02
DE2039064B2 (de) 1972-07-06
CS149924B2 (nl) 1973-08-23
NL7012074A (nl) 1971-02-16
ZA705605B (en) 1971-04-28

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