DE2039064C3 - Adjustable guide vane in a gas turbine with an axial flow - Google Patents
Adjustable guide vane in a gas turbine with an axial flowInfo
- Publication number
- DE2039064C3 DE2039064C3 DE2039064A DE2039064A DE2039064C3 DE 2039064 C3 DE2039064 C3 DE 2039064C3 DE 2039064 A DE2039064 A DE 2039064A DE 2039064 A DE2039064 A DE 2039064A DE 2039064 C3 DE2039064 C3 DE 2039064C3
- Authority
- DE
- Germany
- Prior art keywords
- blade
- guide vane
- compression spring
- bearing bush
- adjusting shaft
- 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
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Support Of The Bearing (AREA)
- Supercharger (AREA)
Description
3535
Die Erfindung betrifft eine verstellbare Leitschaufel in einer axial durchströmten Gasturbine mit einer nachgeschalteten, vom Gaserzeuger unabhängigen Arbeitsturbine, wobei die Leitschaufel innerhalb eines Leitschaufelkranzes vor dieser Arbeitsturbine angeordnet und in einem äußeren Gehäuseteil an ihrer Verstellwelle in Lagerbüchsen fliegend gelagert ist und wobei über eine, die Verstellwelle umgebende Druckfeder das Schaufelblatt der Leitschaufel mit seiner Stirnfläche gegen eine sphärische Gehäuseflache preßbar ist.The invention relates to an adjustable guide vane in an axially flow-through gas turbine with a downstream power turbine, independent of the gas generator, with the guide vane inside a guide vane ring arranged in front of this power turbine and in an outer housing part on its Adjusting shaft is cantilevered in bearing bushes and with a surrounding the adjusting shaft Compression spring the blade of the guide vane with its end face against a spherical housing surface is compressible.
Eine derartige verstellbare Leitschaufel ist aus der britischen Patentschrift 705 150 bekannt.Such an adjustable guide vane is known from British patent specification 705,150.
Bei der bekannten verstellbaren Leitschaufel ist zwischen dem äußeren Gehäuseteil und e;.,m am freien Ende der Versieliwelle angebrachten Verstellhebel eine diese Weile umschließende Druckfeder angebracht, mit welcher das Schaufelblatt ständig in Anlage gegen die sphärische Innenfläche des äußeren Gehäuseteils gehalten wird, (legen das radial innere Ende je zweier benachbarter Schaufeln wirkt ferner ein in einem zentralen Gehäuse geführter, von Druckluft Ih cUifschlagbarcr segmentförmiger Kolben mit sphärischer Oberfläche, durch welche die Schaufeln im Betrieb der Turbine gegen die Innenfläche des alitieren Gehäuses verspannt werden. Um die beidseitige Reibung bei der Verstellung der Schaufelblätter zu vermeiden, liegen diese jedoch nur im ien- 5s tralen Bereich um die Verstellachse gegen den Kolben wie auch das äußere Gehäuse an, wodurch Schwingungen am inneren Schaufelende nicht wirksam vermieden werden können, zumal auch der segmentförmige Kolben durch seine Führungslose im 6U eingestellten Lag: Gehäuse mitschwingen kann. Beim Anfahren fehlt Schwingungen.In the known adjustable guide vane, between the outer housing part and e; The radially inner end of each of two adjacent blades is also acted upon by a segment-shaped piston with a spherical surface, guided by compressed air in a central housing, through which the blades are braced against the inner surface of the alloyed housing during operation of the turbine To avoid the blade blades, however, they only rest against the piston and the outer housing in the central area around the adjustment axis, which means that vibrations at the inner blade end cannot be effectively avoided, especially since the segment-shaped piston with its guide slack in the 6 U entered Lag: Housing can resonate. There are no vibrations when starting.
die Stirnfläche des Schaufelblattes an seiner Spitze sich gegen eine sphärische Gegenfläche eines v· ;nthe end face of the blade at its tip is against a spherical mating surface of a v ·; n
Leitschaufelkranz umgebenen Gehäuseteils preßt.Guide vane ring surrounding the housing part presses.
Ein Ausführunp,sbeispiel der Erfindung wird nachstehend an Hand der Zeichmung näher erläutert, in welcher ein Axialschnitt durch eine Gasturbine Im Bereich einer verstellbaren Leitschaufel dargestelltAn embodiment of the invention is explained in more detail below with reference to the drawing, in which an axial section through a gas turbine is shown in the area of an adjustable guide vane
3c ist. Die in ihrer Gesamtheit mit 10 bezeichnete I.eiischaufel besteht aus einem Schaufelblatt 16 und einer mit einem Lagerbund versehenen Verstellwelle !8, auf deren freies Ende ein Ritzel 19 aufgekeilt ist. Die radial innere Endfläche 20 und die radial äußere Endfläche des Schaufelblatts 16 sind sphärisch gestaltet und schmiegen sich dadurch ungeachtet der Drohstellung der Lei.schaufel auf ihrer gesamten Länge unmittelbar oder mit kleinstem Spiel an die entsprechend gestalteten Gegenflächen eines inneren Geliäu-3c is. The I.eiischaufel designated in its entirety with 10 consists of a blade 16 and an adjusting shaft provided with a bearing collar! 8, a pinion 19 is keyed onto its free end. The radially inner end surface 20 and the radially outer End surfaces of the airfoil 16 are spherical in shape and thus snuggle up over its entire length regardless of the threatening position of the Lei.schaufel directly or with the slightest play on the correspondingly designed opposing surfaces of an inner Geliäu-
4u seteiK 12 bzw. eines äußeren Gehäuseteils an. 4 u seteiK 12 or an outer housing part.
Der Lagerbund 17 ist drehbar in einer festen Lagerbuchse 24 geführt, und eine weitere feste Lager· büchse 25 bildet radial weiter außen ein zweites Lager für die Verstellwelle 18. Die beiden Lageibüchsen 24 und 25 sind in die Bohrung einer am äußeren Gehäuseteil ansetzende 1 ortsfesten Nabe 26 eingesetzt. The bearing collar 17 is rotatably guided in a fixed bearing bush 24, and another fixed bearing Bushing 25 forms a second bearing for the adjusting shaft 18 radially further outwards. The two position bushings 24 and 25 are inserted into the bore of a stationary hub 26 attached to the outer housing part.
Zwischen der Lagerbuchse 25 und einer gegen den vom Lagerbund 17 gebildeten Absatz 21 anliegenden Scheibe 28 stützt sich eine die Verstellwelle 18 umschließende Druckfeder 29 ab. Die Lagerbüchse 25 ist innerhalb der Nabe 26 durch einen Sprengring 30 gesichert, der in eine Ringnut in der Bohrung der Nabe 26 eingesetzt ist. Die Druckfeder 29 stellt siher, daß die radial innere Stirnfläche 20 des Schau-Between the bearing bush 25 and a shoulder 21 formed by the bearing collar 17 resting against it Disk 28 is supported by a compression spring 29 surrounding the adjusting shaft 18. The bearing bush 25 is secured within the hub 26 by a snap ring 30 which is in an annular groove in the bore of the Hub 26 is used. The compression spring 29 ensures that the radially inner end face 20 of the viewing
felblatts 16 auf ihrer gesamten Länge ständig an der ortsfesten sphärischen Gegenfläche des Gehäuseteils 22 unter Druck anliegt. Die dadurch entstehende Reibungskraft sichert lins Schaufelblatt in der jeweils und verhindert wirkungsvollfelblatts 16 constantly on the entire length stationary spherical counter surface of the housing part 22 rests under pressure. The resulting frictional force secures lins shovel blade in each and effectively prevents
Hierzu 1 Blatt Zeichnungen1 sheet of drawings
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR6928154A FR2055780A1 (en) | 1969-08-14 | 1969-08-14 |
Publications (3)
Publication Number | Publication Date |
---|---|
DE2039064A1 DE2039064A1 (en) | 1971-09-02 |
DE2039064B2 DE2039064B2 (en) | 1972-07-06 |
DE2039064C3 true DE2039064C3 (en) | 1974-05-09 |
Family
ID=9039087
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE2039064A Expired DE2039064C3 (en) | 1969-08-14 | 1970-08-06 | Adjustable guide vane in a gas turbine with an axial flow |
Country Status (12)
Country | Link |
---|---|
US (1) | US3685921A (en) |
AT (1) | AT309913B (en) |
CA (1) | CA940051A (en) |
CH (1) | CH520267A (en) |
CS (1) | CS149924B2 (en) |
DE (1) | DE2039064C3 (en) |
ES (1) | ES382608A1 (en) |
FR (1) | FR2055780A1 (en) |
GB (1) | GB1313938A (en) |
NL (1) | NL7012074A (en) |
SE (1) | SE360425B (en) |
ZA (1) | ZA705605B (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4213716A1 (en) * | 1992-04-25 | 1993-10-28 | Asea Brown Boveri | Turbine with direct axial flow - has guide blades, which are axially movable in adjusting axis |
DE102007021448B4 (en) * | 2006-05-18 | 2012-06-28 | Man Diesel & Turbo Se | Diaphragm for an exhaust gas turbocharger operated with heavy oil reciprocating internal combustion engine |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA1034509A (en) * | 1975-10-14 | 1978-07-11 | John Korta | Vane rotator assembly for a gas turbine |
CA1052231A (en) * | 1976-04-22 | 1979-04-10 | Dominion Engineering Works Limited | Water turbine bearing seal |
US4150915A (en) * | 1976-12-23 | 1979-04-24 | Caterpillar Tractor Co. | Variable geometry turbine nozzle |
DE2835349C2 (en) * | 1978-08-11 | 1979-12-20 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Adjustable grille for highly loaded compressors, especially of gas turbine engines |
DE2931766C2 (en) * | 1979-08-04 | 1982-08-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Sealing device for the free blade ends of an adjustable diffuser of a gas turbine |
FR2599785B1 (en) * | 1986-06-04 | 1990-10-12 | Snecma | VARIABLE SETTING AIR INTAKE DIRECTOR FOR TURBOJET |
GB2206381B (en) * | 1987-06-30 | 1991-10-09 | Rolls Royce Plc | A variable stator vane arrangement for a compressor |
DE4100224C2 (en) * | 1991-01-07 | 1994-05-19 | Daimler Benz Ag | Mounting a gas turbine diffuser in a turbine housing |
US6394766B1 (en) * | 1999-11-01 | 2002-05-28 | James G. Gill | Fan with adjustable guide vanes |
FR2814205B1 (en) | 2000-09-18 | 2003-02-28 | Snecma Moteurs | IMPROVED FLOW VEIN TURBOMACHINE |
ITTO20010445A1 (en) * | 2001-05-11 | 2002-11-11 | Fiatavio Spa | STATOR OF A VARIABLE GEOMETRY AXIAL TURBINE FOR AIRCRAFT APPLICATIONS. |
DE10311205B3 (en) * | 2003-03-14 | 2004-09-16 | Man B & W Diesel Ag | Guiding device for a radial turbine of a turbocharger of a lifting piston I.C. engine operating with heavy oil has blades with shafts positioned in a housing part of the device facing a compressor of the turbocharger |
ITMI20032388A1 (en) * | 2003-12-05 | 2005-06-06 | Nuovo Pignone Spa | VARIABLE NOZZLE FOR A GAS TURBINE. |
DE102005040574A1 (en) * | 2005-08-26 | 2007-03-15 | Rolls-Royce Deutschland Ltd & Co Kg | Gap control device for a gas turbine |
US8534990B2 (en) * | 2009-11-11 | 2013-09-17 | Hamilton Sundstrand Corporation | Inlet guide vane drive system with spring preload on mechanical linkage |
Family Cites Families (4)
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 |
CH360074A (en) * | 1957-10-31 | 1962-02-15 | Maschf Augsburg Nuernberg Ag | Diffuser with adjustable blades during operation, especially for gas turbines |
US3013771A (en) * | 1960-10-18 | 1961-12-19 | Chrysler Corp | Adjustable nozzles for gas turbine engine |
GB1211447A (en) * | 1968-09-17 | 1970-11-04 | Leyland Gas Turbines Ltd | Turbine having variable angle nozzle guide vanes |
-
1969
- 1969-08-14 FR FR6928154A patent/FR2055780A1/fr not_active Withdrawn
-
1970
- 1970-08-04 CH CH1169270A patent/CH520267A/en not_active IP Right Cessation
- 1970-08-05 US US61205A patent/US3685921A/en not_active Expired - Lifetime
- 1970-08-06 GB GB3791770A patent/GB1313938A/en not_active Expired
- 1970-08-06 DE DE2039064A patent/DE2039064C3/en not_active Expired
- 1970-08-08 ES ES382608A patent/ES382608A1/en not_active Expired
- 1970-08-10 AT AT726170A patent/AT309913B/en not_active IP Right Cessation
- 1970-08-12 CS CS5602A patent/CS149924B2/cs unknown
- 1970-08-12 SE SE11003/70A patent/SE360425B/xx unknown
- 1970-08-13 ZA ZA705605A patent/ZA705605B/en unknown
- 1970-08-14 NL NL7012074A patent/NL7012074A/xx not_active Application Discontinuation
- 1970-08-14 CA CA090,822A patent/CA940051A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4213716A1 (en) * | 1992-04-25 | 1993-10-28 | Asea Brown Boveri | Turbine with direct axial flow - has guide blades, which are axially movable in adjusting axis |
DE102007021448B4 (en) * | 2006-05-18 | 2012-06-28 | Man Diesel & Turbo Se | Diaphragm for an exhaust gas turbocharger operated with heavy oil reciprocating internal combustion engine |
Also Published As
Publication number | Publication date |
---|---|
ZA705605B (en) | 1971-04-28 |
SE360425B (en) | 1973-09-24 |
US3685921A (en) | 1972-08-22 |
FR2055780A1 (en) | 1971-04-30 |
NL7012074A (en) | 1971-02-16 |
DE2039064A1 (en) | 1971-09-02 |
CS149924B2 (en) | 1973-08-23 |
GB1313938A (en) | 1973-04-18 |
ES382608A1 (en) | 1974-12-16 |
CH520267A (en) | 1972-03-15 |
AT309913B (en) | 1973-09-10 |
DE2039064B2 (en) | 1972-07-06 |
CA940051A (en) | 1974-01-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
C3 | Grant after two publication steps (3rd publication) | ||
E77 | Valid patent as to the heymanns-index 1977 | ||
8339 | Ceased/non-payment of the annual fee |