DE1278178B - Inlet guide vane ring for axial compressors of gas turbine engines - Google Patents
Inlet guide vane ring for axial compressors of gas turbine enginesInfo
- Publication number
- DE1278178B DE1278178B DER32617A DER0032617A DE1278178B DE 1278178 B DE1278178 B DE 1278178B DE R32617 A DER32617 A DE R32617A DE R0032617 A DER0032617 A DE R0032617A DE 1278178 B DE1278178 B DE 1278178B
- Authority
- DE
- Germany
- Prior art keywords
- guide vane
- wall
- inlet guide
- vane ring
- transverse
- 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.)
- Withdrawn
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
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
DEUTSCHESGERMAN
PATENTAMTPATENT OFFICE
AUSLEGESCHRIFTEDITORIAL
Int. Cl.:Int. Cl .:
F02cF02c
Deutsche Kl.: 46 f-8/03 German class: 46 f- 8/03
Nummer:
Aktenzeichen:
Anmeldetag:
Auslegetag:Number:
File number:
Registration date:
Display day:
P 12 78 178.1-13 (R 32617)P 12 78 178.1-13 (R 32617)
3. Mai 1962May 3, 1962
19. September 196819th September 1968
Die Erfindung betrifft einen Eintrittsleitschaufelkranz für Axialverdichter von Gasturbinentriebwerken, insbesondere Hubtriebwerken für Flugzeuge; bei dem die gegebenenfalls verdickten radial inneren und äußeren Schaufelenden durch querschnittsgleiche Schlitze in der radial inneren und äußeren Kanalwand gesteckt und dort befestigt sind, wobei die Kanalwände in radialem Abstand koaxiale Verstärkungswände und verbindende ringförmige Querwände aufweisen.The invention relates to an inlet guide vane ring for axial compressors of gas turbine engines, in particular lifting engines for aircraft; in which the optionally thickened radially inner and outer blade ends through slots with the same cross-section in the radially inner and outer channel walls are plugged and fastened there, the channel walls at a radial distance from coaxial reinforcing walls and have connecting annular transverse walls.
Bei einer aus der britischen Patentschrift 797 445 bekannten Konstruktion dieser Art sind die Leitschaufeln an ihren Enden in sie aus ihrem gesamten Umfang umschließenden Schlitzen der Kanalwände gehaltert. Zur Erzielung der notwendigen Stabilität werden dabei erhebliche Wandstärken der Kanalwände benötigt.In a construction of this type known from British Patent 797,445, the guide vanes are at their ends in them from their entire circumference enclosing slots in the channel walls held. In order to achieve the necessary stability, considerable wall thicknesses of the duct walls are required needed.
Der Erfindung liegt die Aufgabe zugrunde, eine Schaufelbefestigung für eine Anordnung der eingangs bezeichneten Art anzugeben, deren Stabilität nicht mehr ausschließlich von der Wandstärke der Kanalwände abhängig ist, so daß diese Kanalwände im Hinblick auf die gewünschte Gewichtsverminderung auch dünner ausgeführt werden können.The invention is based on the object of a blade attachment for an arrangement of the above specified type, the stability of which no longer depends solely on the wall thickness of the Channel walls is dependent, so that these channel walls in terms of the desired weight reduction can also be made thinner.
Zur Lösung der Erfindungsaufgabe wird vorgeschlagen, daß die Eintrittskanten und Austrittskanten der Schaufelenden zusätzlich in an sich bekannter Weise in radialen Schlitzen liegen, die in den Querwänden ausgebildet sind.To achieve the object of the invention, it is proposed that the leading edges and trailing edges the blade ends are also in a known manner in radial slots that are in the transverse walls are trained.
Die Befestigung von Schaufelenden in radialen Schlitzen von Querwänden ist an sich bekannt. Dabei sind an den Schaufelenden jedoch sehr breite Fuß- und Wurzelteile angeformt, die im fertigmontierten Zustand eine zusammengesetzte Ringplattform bilden. Mit dieser bekannten Lösung ist somit dem Problem der Gewichtsersparnis nicht beizukommen.The fastening of blade ends in radial slots in transverse walls is known per se. Included However, very wide foot and root parts are formed on the blade ends, which are fully assembled State form a composite ring platform. With this known solution is thus the Problem of weight saving not to be solved.
Die erfindungsgemäße Lösung vereinigt die Vorteile einer stabilen Halterung der Schaufelenden einerseits und der Möglichkeit einer Wandstärkeverminderung der Kanalwände andererseits.The solution according to the invention combines the advantages of a stable mounting of the blade ends on the one hand and the possibility of reducing the wall thickness of the duct walls on the other hand.
Vorzugsweise bilden die eine Querwand den Querschenkel und die radial innere Kanalwand und die Verstärkungswand die Längsschenkel eines U-Ringes; die andere Querwand ist hierbei in die Längsschenkel eingepaßt.Preferably, the one transverse wall form the transverse leg and the radially inner channel wall and the reinforcement wall the longitudinal legs of a U-ring; the other transverse wall is here in the Longitudinal leg fitted.
Nach vorteilhafter Ausführungsform ist der U-Ring in an sich bekannter Weise mit einem Nebenteil verbunden, der ein Triebwerklager trägt.According to an advantageous embodiment, the U-ring is connected to a secondary part in a manner known per se, which carries an engine bearing.
Es kann zweckmäßig sein, wenn wenigstens einige Teile des Eintrittsleitschaufelkranzes in an sich bekannter Weise aus Kunstharz bestehen und durch Kleben miteinander verbunden sind.It can be useful if at least some parts of the inlet guide vane ring are known per se Way made of synthetic resin and are connected to each other by gluing.
Eintrittsleitschaufelkranz für Axialverdichter
von GasturbinentriebwerkenInlet guide vane ring for axial compressors
of gas turbine engines
Anmelder:Applicant:
Rolls-Royce Limited,Rolls-Royce Limited,
Derby, Derbyshire (Großbritannien)Derby, Derbyshire (UK)
Vertreter:Representative:
Dipl.-Ing. F. Weickmann,Dipl.-Ing. F. Weickmann,
Dipl.-Ing. H. WeickmannDipl.-Ing. H. Weickmann
und Dipl.-Phys. Dr. K. Fincke, Patentanwälte,and Dipl.-Phys. Dr. K. Fincke, patent attorneys,
8000 München, Möhlstr. 228000 Munich, Möhlstr. 22nd
Als Erfinder benannt:Named as inventor:
Norman Robert Robinson, Derby, Derbyshire;Norman Robert Robinson, Derby, Derbyshire;
John Michael Sterer Keen,John Michael Sterer Keen,
Allestree, Derby, Derbyshire (Großbritannien)Allestree, Derby, Derbyshire (UK)
Beanspruchte Priorität:Claimed priority:
Großbritannien vom 3. Mai 1961 (16 090)Great Britain May 3, 1961 (16 090)
ZZ
Eine beispielsweise Ausführungsform der Erfindung soll nun an Hand der Zeichnungen näher erläutert
werden; von diesen zeigt
F i g. 1 in einem Teilschnitt durch das Triebwerk den erfindungsgemäßen Eintrittsleitschaufelkranz,An example embodiment of the invention will now be explained in more detail with reference to the drawings; of these shows
F i g. 1 shows the inlet guide vane ring according to the invention in a partial section through the engine,
F i g. 2 eine Schnittansicht in Richtung des Pfeils 2 der F i g. 1 gesehen,F i g. 2 is a sectional view in the direction of arrow 2 in FIG. 1 seen
F i g. 3 und 4 Teildarstellungen von Schnitten längs der Linien 3-3 bzw. 4-4 in Fig. 1.F i g. 3 and 4 partial representations of sections along the lines 3-3 and 4-4, respectively, in FIG. 1.
Das in F i g. 1 dargestellte Gehäuse 11 des Axialverdichters eines insbesondere als Hubtriebwerk für Flugzeuge geeigneten Gasturbinentriebwerkes umfaßt die Gehäusewand 21, 22. Diese umgeben die Einlaßleitschaufeln 14, die übrigen Leitschaufeln und die Laufschaufeln des Verdichters 15 und bestehen aus verstärktem Kunstharz, beispielsweise einem mit Glasfasern ausgesteiften Epoxy- oder Phenolharz.The in Fig. 1 illustrated housing 11 of the axial compressor, in particular as a lifting mechanism for Aircraft suitable gas turbine engine comprises the casing wall 21, 22. These surround the inlet guide vanes 14, the remaining guide vanes and the rotor blades of the compressor 15 and consist of reinforced synthetic resin, for example an epoxy or phenolic resin reinforced with glass fibers.
Die Einlaßstreben 12, die Einlaßleitschaufeln 14, die übrigen Leitschaufeln und die Laufschaufeln des Verdichters 15 bestehen ebenfalls aus einem solchen verstärkten Kunstharz.The inlet struts 12, the inlet guide vanes 14, the remaining guide vanes and the blades of the Compressor 15 are also made of such a reinforced synthetic resin.
809 617/134809 617/134
Die radial äußeren Enden 23 der Einlaßleitschaufeln 14 sind verdickt und mit ihrer Eintritts- und Austrittskante in in Winkelabständen vorgesehenen Schlitzen24, 25 (Fig. 2) eingeklebt, die an in axialem Abstand angeordneten ringförmigen Querwänden 26, 27 angebracht sind. Die Querwände 26, 27 bestehen aus verstärktem Kunstharz und sind an der Gehäusewand 21 angeklebt, welche Öffnungen 28 hat, durch welche die Einlaßleitschaufeln 14 durchgesteckt sind.The radially outer ends 23 of the inlet guide vanes 14 are thickened and with their inlet and The trailing edge is glued into slots 24, 25 (Fig. 2) provided at angular intervals, which are attached to the axial Spaced annular transverse walls 26, 27 are attached. The transverse walls 26, 27 consist of reinforced synthetic resin and are glued to the housing wall 21, which openings 28 has through which the inlet guide vanes 14 are inserted.
Die Querwand 27 ist durch Klebung und einen Stift30 (Fig. 1) mit einer Querwand31 aus verstärktem Kunstharz verbunden, welche an der Gehäusewand 22 angeklebt ist.The transverse wall 27 is reinforced with a transverse wall 31 by gluing and a pin 30 (Fig. 1) Resin bonded, which is glued to the housing wall 22.
Die Querwände 26, 27 und 31 werden von einer äußeren Gehäusewand 32 aus verstärktem Kunstharz umschlossen und sind an dieser angeklebt.The transverse walls 26, 27 and 31 are made of reinforced synthetic resin by an outer housing wall 32 enclosed and glued to this.
Die radial inneren Enden 33 der Einlaßleitschaufeln 14 sind ebenfalls verdickt und an ihrer Eintritts- und Austrittskante in Schlitzen 34, 35 eingeklebt, die an in axialem Abstand angeordneten Querwänden 36, 37 in Winkelabständen angebracht sind.The radially inner ends 33 of the inlet guide vanes 14 are also thickened and at their inlet and the trailing edge is glued into slots 34, 35 on axially spaced transverse walls 36, 37 are attached at angular intervals.
Die Querwand 36 bildet die axiale Endwand eines Rings40 mit U-förmigem Querschnitt (Fig. 1) und mit sich axial erstreckenden, in radialem Abstand befindlichen äußeren und inneren Wandungen 41, 42.The transverse wall 36 forms the axial end wall of a ring 40 with a U-shaped cross section (FIG. 1) and with axially extending, radially spaced outer and inner walls 41, 42.
Die Teile 37 und 40 bestehen aus verstärktem Kunstharz. Die Querwand 37 sitzt zwischen der inneren und äußeren Wandung 41, 42 des Rings 40 und ist an diese angeklebt.The parts 37 and 40 are made of reinforced synthetic resin. The transverse wall 37 sits between the inner and outer walls 41, 42 of the ring 40 and is glued to them.
Die radial inneren Schaufelenden 33 gehen so weit durch Öffnungen 43 (F i g. 4) in der Kanalwand 41, daß sie an der Verstärkungswand 42 anliegen.The radially inner blade ends 33 go so far through openings 43 (FIG. 4) in the duct wall 41, that they rest against the reinforcement wall 42.
Die Ringe 40 und 37 bilden zusammen einen äußeren Nabenteil, in welchem ein innerer Nabenteil 44 aus verstärktem Kunstharz eingeklebt ist. In diesem ist ein Lagergehäuse 45 aus verstärktem Kunstharz eingeklebt. Dieses Lagergehäuse trägt den Außenring 47 eines Wälzlagers 45 für die Läuferwelle. The rings 40 and 37 together form an outer hub part in which an inner hub part 44 made of reinforced synthetic resin is glued in place. In this is a bearing housing 45 made of reinforced synthetic resin glued in. This bearing housing carries the outer ring 47 of a roller bearing 45 for the rotor shaft.
Am inneren Nabenteil 44 ist eine ringförmige Dichtungsplatte 51 angeschraubt, welche eine Labyrinth-Wellendichtung 52 trägt.An annular sealing plate 51, which is a labyrinth shaft seal, is screwed to the inner hub part 44 52 carries.
Claims (4)
Deutsche Patentschriften Nr. 1009 349, 966 949, 700;Considered publications:
German Patent Nos. 1009 349, 966 949, 700;
944756;French patent specification No. 1201329,
944756;
106, 728 670;British patents nos. 805 545, 797 445,
106, 728 670;
834 537, 2 749 026, 2 605 997.U.S. Patents Nos. 2,951,631, 2,868,439,
834 537, 2 749 026, 2 605 997.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB26021/66A GB1096257A (en) | 1966-06-10 | 1966-06-10 | Gas turbine engine |
Publications (1)
Publication Number | Publication Date |
---|---|
DE1278178B true DE1278178B (en) | 1968-09-19 |
Family
ID=10237120
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DER32617A Withdrawn DE1278178B (en) | 1966-06-10 | 1962-05-03 | Inlet guide vane ring for axial compressors of gas turbine engines |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE1278178B (en) |
FR (1) | FR1339521A (en) |
GB (1) | GB1096257A (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2647502B1 (en) * | 1989-05-23 | 1991-09-13 | Europ Propulsion | TURBINE DISTRIBUTOR FOR TURBO-REACTOR AND MANUFACTURING METHOD THEREOF |
Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR944756A (en) * | 1946-04-05 | 1949-04-14 | Rolls Royce | Improvements to the guide vanes of compressors and axial type turbines |
DE843700C (en) * | 1950-01-21 | 1952-07-10 | Canadian Patents Dev | Storage for the nozzle guide vanes of turbines |
GB728670A (en) * | 1950-08-01 | 1955-04-27 | Rolls Royce | Improvements in or relating to structural elements for turbo-machines such as compressors or turbines of gas-turbine engines |
US2749026A (en) * | 1951-02-27 | 1956-06-05 | United Aircraft Corp | Stator construction for compressors |
GB758106A (en) * | 1952-12-22 | 1956-09-26 | Gen Motors Corp | Improvements in turbine nozzles |
DE966949C (en) * | 1943-01-16 | 1957-09-19 | Karl Wernert | Housing made of plastic to be cast or pressed for centrifugal pumps, blowers or the like. |
US2834537A (en) * | 1954-01-18 | 1958-05-13 | Ryan Aeronautical Co | Compressor stator structure |
GB797445A (en) * | 1955-10-18 | 1958-07-02 | Rolls Royce | Improvements in or relating to rotary fluid machines, for example turbines and compressors |
GB805545A (en) * | 1956-02-06 | 1958-12-10 | Rolls Royce | Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines |
US2868439A (en) * | 1954-05-07 | 1959-01-13 | Goodyear Aircraft Corp | Plastic axial-flow compressor for gas turbines |
FR1201329A (en) * | 1957-08-16 | 1959-12-29 | United Aircraft Corp | Stator vanes |
US2951631A (en) * | 1956-01-25 | 1960-09-06 | Fairchild Engine & Airplane | Engine accessory drive |
-
1962
- 1962-04-25 FR FR895507A patent/FR1339521A/en not_active Expired
- 1962-05-03 DE DER32617A patent/DE1278178B/en not_active Withdrawn
-
1966
- 1966-06-10 GB GB26021/66A patent/GB1096257A/en not_active Expired
Patent Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE966949C (en) * | 1943-01-16 | 1957-09-19 | Karl Wernert | Housing made of plastic to be cast or pressed for centrifugal pumps, blowers or the like. |
US2605997A (en) * | 1946-04-05 | 1952-08-05 | Rolls Royce | Mounting for the guide vanes of axial-flow compressors and turbines |
FR944756A (en) * | 1946-04-05 | 1949-04-14 | Rolls Royce | Improvements to the guide vanes of compressors and axial type turbines |
DE843700C (en) * | 1950-01-21 | 1952-07-10 | Canadian Patents Dev | Storage for the nozzle guide vanes of turbines |
GB728670A (en) * | 1950-08-01 | 1955-04-27 | Rolls Royce | Improvements in or relating to structural elements for turbo-machines such as compressors or turbines of gas-turbine engines |
US2749026A (en) * | 1951-02-27 | 1956-06-05 | United Aircraft Corp | Stator construction for compressors |
GB758106A (en) * | 1952-12-22 | 1956-09-26 | Gen Motors Corp | Improvements in turbine nozzles |
US2834537A (en) * | 1954-01-18 | 1958-05-13 | Ryan Aeronautical Co | Compressor stator structure |
US2868439A (en) * | 1954-05-07 | 1959-01-13 | Goodyear Aircraft Corp | Plastic axial-flow compressor for gas turbines |
GB797445A (en) * | 1955-10-18 | 1958-07-02 | Rolls Royce | Improvements in or relating to rotary fluid machines, for example turbines and compressors |
US2951631A (en) * | 1956-01-25 | 1960-09-06 | Fairchild Engine & Airplane | Engine accessory drive |
GB805545A (en) * | 1956-02-06 | 1958-12-10 | Rolls Royce | Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines |
FR1201329A (en) * | 1957-08-16 | 1959-12-29 | United Aircraft Corp | Stator vanes |
Also Published As
Publication number | Publication date |
---|---|
FR1339521A (en) | 1963-10-11 |
GB1096257A (en) | 1967-12-20 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
E77 | Valid patent as to the heymanns-index 1977 | ||
EGA | New person/name/address of the applicant | ||
EHJ | Ceased/non-payment of the annual fee |