US3652177A - Installation for the support of pivotal guide blades - Google Patents

Installation for the support of pivotal guide blades Download PDF

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Publication number
US3652177A
US3652177A US38679A US3652177DA US3652177A US 3652177 A US3652177 A US 3652177A US 38679 A US38679 A US 38679A US 3652177D A US3652177D A US 3652177DA US 3652177 A US3652177 A US 3652177A
Authority
US
United States
Prior art keywords
blade
installation according
shaft
annular groove
bearing
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
US38679A
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English (en)
Inventor
Wolf Loebel
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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
Priority claimed from DE19691926327 external-priority patent/DE1926327C/de
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Application granted granted Critical
Publication of US3652177A publication Critical patent/US3652177A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

Definitions

  • the present invention relates to an installation for the support of pivotal guide blades of turbo-machines, especially of gas turbines, whereby chambers or passages are provided in a bearing support, through which flows cooling air.
  • Particular difficulties have to be overcome in the support of pivotal guide blades of gas turbines, by reason of the large temperature range in which a satisfactory operation must be assured at all times, which difficulties consist in that the bearing clearance necessary for the pivoting movement has to be maintained notwithstanding the considerable thermal expansions.
  • a blade shaft constructed as adjusting or actuating shaft be provided with annular grooves in its central bearing portion and at the blade end, which are connected with each other by a thread with cylindrical external surfaces, whereby the central annular groove is in communication with the chambers or passages conducting the cooling air and the annular groove at the blade side is in communication with the guide blade space of the machine.
  • the cooling air which can be derived, for example, from a suitable compressor stage or from a similar air supply, flows through the central bore into the central annular groove of the blade shaft and from there by way of the thread to the blade end of the shaft where it flows off into the guide blade space by way of the second bore.
  • the particular advantage of this arrangement resides in that the bearing support is effectively cooled at its hottest place; namely, at the blade shaft itself.
  • a further advantage resides in that the blade shaft and bearing bore are kept by the cooling system approximately at the same operating temperature at their contact places whereby the bearing clearance which exists with a cold machine, remains approximately constant over the entire operating range (temperature range) of the machine.
  • the blade shaft includes, starting from its central annular groove toward the outside, a labyrinth seal having cylindrical external surfaces and consisting of a large number of annular grooves.
  • the labyrinth is advantageously formed by a number of annular grooves of rectangular cross-section.
  • the blade shaft is constructed as hollow shaft which results in a relatively slight heat flow from the blade through the shaft so that the ratio of heat transferred to the bearing place to the heat removed by cooling can be kept small.
  • a bearing bush with good anti-friction properties is inserted between the bearing support and the blade shaft, which bush is provided with inlet and outlet bores or ports for the cooling air corresponding to the bores in the bearing support.
  • a bearing bush between housing and adjusting shaft offers the advantage that a material can be selected for the bearing bush which, first of all, has good anti-friction properties that do not change or change only slightly over a certain temperature range, without requiring at the same time high strength properties as are required, for example, in connection with the housing material.
  • the good anti-friction properties must be ensured by a suitable material combination since a reduction of the friction by, a lubricant must be considered impractical,
  • a favorable low friction clearance conditioned on the material can be attained at the blade adjusting shaft which results correspondingly in slight adjusting forces (moments).
  • the bearing bush is provided at its blade end with an offset of reduced diametric dimension so that an inwardly open annular space results between the housing bore and bearing bush, through which the cooling air leaving the bearing bush is conducted into the main gas stream of the turbo-machine. Retuming the cooling air into the guide blade space through such an annular space offers the advantage that any combustion residues which are deposited in the annular gap between the upper guide blade end and the housing bore, are constantly blown off by the inwardly directed air stream and are returned to the main gas stream.
  • the blade shaft is provided at its blade end with an annular collar that abuts at the inner end face of the housing or of the bearing bush.
  • An outwardly directed pressure force results at the annular collar from the gas pressure in the guide blade space which presses the annular collar against the end surface of the housing or bearing bush so that a good seal of the guide blade space with respect to the bearing place is realized.
  • a spring prestressed in the axial direction is provided which is supported on the outer side of the bearing support, on the one hand, and on the blade shaft, on the other.
  • This spring pulls the blade shaft outwardly with its prestress so that it causes an abutment of the annular collar of the blade shaft at the inner end face of the bearing bush or housing also with a slight excess pressure in the guide blade space and thus assures a good sealing effect.
  • the single FIGURE is a partial cross-sectional view through a guide blade adjusting mechanism of a gas turbine with a bearing bush in accordance with the present invention.
  • a bearing bush 3 is securely fitted into a bore 21 provided in a housing 2 forming a bearing support.
  • a bore or port 5 is disposed approximately in the center of the bush 3 which is in communication by way of a further bore or port 25 in the housing 2 with a cooling air passage 4 of the housing.
  • the bush 3 is provided with a reduced diametric portion forming an offset 23 so that an annular space 22 remains between the bore 21 and the bush 3 at this place.
  • One or several radial bores 6 of the bush 3 terminate in this annular space 22.
  • the shaft of the guide blade 9 constructed as actuating or adjusting shaft 7 is supported in the bush 3.
  • the guide blade shaft 7 is provided at its blade end with an annular collar 8 and adjoining the same with an annular groove 18.
  • the shaft 7 is provided in the central area thereof, at the place of the bore 5 of the bush 3, with an annular groove 16.
  • This annular groove 16 is in communication with the annular groove 18 by way of several threads of trapezoidal cross-section such as ACME thread form.
  • the support of the shaft 7 takes place at the cylindrical outer surfaces of the thread 17 within the bearing bush 3.
  • the shaft surface Extending outwardly from the annular groove 16, the shaft surface is provided with a number of annular grooves 20 constructed as labyrinth seal.
  • a pivot or actuating lever 13 is clampingly secured to the outer end 12 of the blade shaft 7.
  • this adjusting lever 13 takes place by an adjusting or actuating ring 14 arranged at the housing 2.
  • An axially prestressed disk or cup spring is provided between the lever 13 and the outer end face of the bush 3, on which rests a closure disk or carrying washer 10a; the prestress force of the spring 10 is transmitted by way of the lever 13 to the blade shaft 7 so that the annular collar 8 of the shaft 7 is pressed against the end surface 30 of the bush 3, located at the inner side of the housing.
  • the cooling air flows inwardly and outwardly, following the pressure drop, and more particularly inwardly by way of the thread 17 whereby it cools in an effective manner the blade shaft 7 and the bush 3.
  • the cooling air reaches the annular groove 18 from where'it flows off by way of the bore 6 into the annular space 22 and from there into the main stream duct 1.
  • a very small amount of compressed air flows from the annular groove 16 in the outward direction by way of the labyrinth seal 20 and exits into the atmosphere at the spring 10 by way of gaps.
  • An installation for supporting pivotal guide blades of turbo-machines in which at least one passage is provided in a bearing support through which flows cooling air, characterized in that a blade shaft constructed as an adjusting shaft is provided with annular grooves in its central bearing area and near the blade end thereof, which are in communication with each other by way of a thread, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine.
  • blade shaft is provided near the blade end thereofwith.
  • An installation according to claim 12 characterized in that an axially prestressed spring means is provided which is supported, on the one hand, on the outer side of'the bearing support and, on the other, at the blade shaft.
  • An installation for supporting pivotal guide blades of turbo-machines comprising a blade shaft formed as an adjusting shaft carrying a blade at one end thereof, a bearing support surrounding said shaft and having at least one passage for conducting cooling air, said shaft being provided with an annular groove in its central bearing area and an annular groove near the bladeend thereof, the central annular groove being in communication with the passage conducting the cooling air while the annular groove near the blade end is in communication with the guide blade space of the machine, the portion-of said blade shaft between the central and blade end grooves being provided with a helical thread for communication therebetween.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US38679A 1969-05-23 1970-05-19 Installation for the support of pivotal guide blades Expired - Lifetime US3652177A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19691926327 DE1926327C (de) 1969-05-23 Lagerung schwenkbarer Leitschaufeln

Publications (1)

Publication Number Publication Date
US3652177A true US3652177A (en) 1972-03-28

Family

ID=5734972

Family Applications (1)

Application Number Title Priority Date Filing Date
US38679A Expired - Lifetime US3652177A (en) 1969-05-23 1970-05-19 Installation for the support of pivotal guide blades

Country Status (4)

Country Link
US (1) US3652177A (enrdf_load_stackoverflow)
FR (1) FR2030895A5 (enrdf_load_stackoverflow)
GB (1) GB1249279A (enrdf_load_stackoverflow)
SE (1) SE358441B (enrdf_load_stackoverflow)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3788763A (en) * 1972-11-01 1974-01-29 Gen Motors Corp Variable vanes
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
US4007998A (en) * 1975-08-22 1977-02-15 Carrier Corporation Blade assembly
US4025227A (en) * 1975-06-30 1977-05-24 United Technologies Corporation Variable area turbine
US4522557A (en) * 1982-01-07 1985-06-11 S.N.E.C.M.A. Cooling device for movable turbine blade collars
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US4810165A (en) * 1986-07-09 1989-03-07 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Adjusting mechanism for guide blades of turbo-propulsion units
US4861228A (en) * 1987-10-10 1989-08-29 Rolls-Royce Plc Variable stator vane assembly
US5498128A (en) * 1993-03-25 1996-03-12 Abb Management Ag Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes
US5518365A (en) * 1993-03-25 1996-05-21 Abb Management Ag Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes
US5622473A (en) * 1995-11-17 1997-04-22 General Electric Company Variable stator vane assembly
US20010026758A1 (en) * 2000-04-04 2001-10-04 Man B&W Diesel Aktiengesellschaft Flow duct guide apparatus for an axial flow trubine
US6443694B1 (en) * 1998-05-28 2002-09-03 Abb Rotor machine device
EP1217173A3 (en) * 2000-12-20 2003-10-29 United Technologies Corporation Vane for use in turbo machines
EP1256697A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Stator vane of a variable-geometry turbine
US20040107538A1 (en) * 2002-07-16 2004-06-10 Avio S.P.A. Hinge device for a rotary member of an aircraft engine
US20070160463A1 (en) * 2005-08-26 2007-07-12 Ingo Jahns Gap control arrangement for a gas turbine
US20100018219A1 (en) * 2006-06-01 2010-01-28 Moreno Baldaccini Device for optimizing cooling in gas turbines
US20120093632A1 (en) * 2010-10-15 2012-04-19 General Electric Company Variable turbine nozzle system
US20120121403A1 (en) * 2009-07-20 2012-05-17 Cameron International Corporation Removable throat mounted inlet guide vane
US9200640B2 (en) 2009-11-03 2015-12-01 Ingersoll-Rand Company Inlet guide vane for a compressor
US20160222825A1 (en) * 2013-10-03 2016-08-04 United Technologies Corporation Rotating turbine vane bearing cooling
US20160376916A1 (en) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
US20160376915A1 (en) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
US10711817B2 (en) * 2016-06-14 2020-07-14 EMC IP Holding Company LLC Rod for use in rack and holding device for use in cooperation with rack

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly
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
FR2570133A1 (fr) * 1984-09-12 1986-03-14 Szydlowski Joseph Dispositif d'orientation d'ecoulement d'air en un point quelconque sur toute une hauteur de pale a l'entree d'une roue d'un compresseur axial
GB2339244B (en) 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1770496A (en) * 1916-08-25 1930-07-15 Worthington Pump & Mach Corp Shaft packing
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
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit
US3525574A (en) * 1968-07-26 1970-08-25 Sulzer Ag Vane ring for turbo-engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1770496A (en) * 1916-08-25 1930-07-15 Worthington Pump & Mach Corp Shaft packing
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
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit
US3525574A (en) * 1968-07-26 1970-08-25 Sulzer Ag Vane ring for turbo-engines

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3788763A (en) * 1972-11-01 1974-01-29 Gen Motors Corp Variable vanes
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
US4025227A (en) * 1975-06-30 1977-05-24 United Technologies Corporation Variable area turbine
US4007998A (en) * 1975-08-22 1977-02-15 Carrier Corporation Blade assembly
US4522557A (en) * 1982-01-07 1985-06-11 S.N.E.C.M.A. Cooling device for movable turbine blade collars
US4810165A (en) * 1986-07-09 1989-03-07 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Adjusting mechanism for guide blades of turbo-propulsion units
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US4861228A (en) * 1987-10-10 1989-08-29 Rolls-Royce Plc Variable stator vane assembly
US5498128A (en) * 1993-03-25 1996-03-12 Abb Management Ag Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes
US5518365A (en) * 1993-03-25 1996-05-21 Abb Management Ag Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes
US5622473A (en) * 1995-11-17 1997-04-22 General Electric Company Variable stator vane assembly
US6443694B1 (en) * 1998-05-28 2002-09-03 Abb Rotor machine device
US20010026758A1 (en) * 2000-04-04 2001-10-04 Man B&W Diesel Aktiengesellschaft Flow duct guide apparatus for an axial flow trubine
US6547521B2 (en) * 2000-04-04 2003-04-15 Man B&W Diesel Aktiengesellschaft Flow duct guide apparatus for an axial flow turbine
EP1217173A3 (en) * 2000-12-20 2003-10-29 United Technologies Corporation Vane for use in turbo machines
EP1256697A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Stator vane of a variable-geometry turbine
US20040107538A1 (en) * 2002-07-16 2004-06-10 Avio S.P.A. Hinge device for a rotary member of an aircraft engine
EP1382804A3 (en) * 2002-07-16 2004-09-15 AVIO S.p.A. Hinge device for a rotary member of an aircraft engine
US20070160463A1 (en) * 2005-08-26 2007-07-12 Ingo Jahns Gap control arrangement for a gas turbine
US20100018219A1 (en) * 2006-06-01 2010-01-28 Moreno Baldaccini Device for optimizing cooling in gas turbines
US8453465B2 (en) * 2006-06-01 2013-06-04 Nuovo Pignone, S.P.A. Device for optimizing cooling in gas turbines
US9243648B2 (en) * 2009-07-20 2016-01-26 Ingersoll-Rand Company Removable throat mounted inlet guide vane
US20120121403A1 (en) * 2009-07-20 2012-05-17 Cameron International Corporation Removable throat mounted inlet guide vane
CN102575684A (zh) * 2009-07-20 2012-07-11 卡梅伦国际公司 可移除的安装在喉部的入口引导叶片
US9200640B2 (en) 2009-11-03 2015-12-01 Ingersoll-Rand Company Inlet guide vane for a compressor
US8668445B2 (en) * 2010-10-15 2014-03-11 General Electric Company Variable turbine nozzle system
US20120093632A1 (en) * 2010-10-15 2012-04-19 General Electric Company Variable turbine nozzle system
DE102011054468B4 (de) * 2010-10-15 2021-05-20 General Electric Company Variables Turbinenleitapparatsystem
US20160222825A1 (en) * 2013-10-03 2016-08-04 United Technologies Corporation Rotating turbine vane bearing cooling
US10830096B2 (en) * 2013-10-03 2020-11-10 Raytheon Technologies Corporation Rotating turbine vane bearing cooling
US20160376916A1 (en) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
US20160376915A1 (en) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
US10344616B2 (en) * 2015-06-25 2019-07-09 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
US10711817B2 (en) * 2016-06-14 2020-07-14 EMC IP Holding Company LLC Rod for use in rack and holding device for use in cooperation with rack

Also Published As

Publication number Publication date
DE1926327A1 (de) 1970-12-03
SE358441B (enrdf_load_stackoverflow) 1973-07-30
FR2030895A5 (enrdf_load_stackoverflow) 1970-11-13
GB1249279A (en) 1971-10-13
DE1926327B2 (de) 1972-09-14

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