EP0575017B1 - Turbomachine - Google Patents

Turbomachine Download PDF

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Publication number
EP0575017B1
EP0575017B1 EP93250128A EP93250128A EP0575017B1 EP 0575017 B1 EP0575017 B1 EP 0575017B1 EP 93250128 A EP93250128 A EP 93250128A EP 93250128 A EP93250128 A EP 93250128A EP 0575017 B1 EP0575017 B1 EP 0575017B1
Authority
EP
European Patent Office
Prior art keywords
shaft part
shaft
gear
wheel
expansion screw
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
EP93250128A
Other languages
German (de)
English (en)
Other versions
EP0575017A1 (fr
Inventor
Ernst Rothstein
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.)
Vodafone GmbH
Original Assignee
Mannesmann AG
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 Mannesmann AG filed Critical Mannesmann AG
Publication of EP0575017A1 publication Critical patent/EP0575017A1/fr
Application granted granted Critical
Publication of EP0575017B1 publication Critical patent/EP0575017B1/fr
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
    • 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
    • F01D5/026—Shaft to shaft connections

Definitions

  • the invention relates to a transmission turbomachine according to the preamble of claim 1.
  • the gear element in particular is usually made from an alloyed tempering steel, the surface of which is hardened in the flank area.
  • the problem of choosing the right material arises in the already mentioned LNG compressor in that on the back of the impeller, especially during standstill and in the start-up phase, part of the wave range is also acted on by the frozen gas.
  • both the impeller including the subsequent shaft part could be made in one piece from a low-temperature-resistant steel.
  • the production requires a great deal of machining work, since the outer dimensions of the impeller determine the size of the block to be machined.
  • DE-A-2510287 discloses a gas turbine with an autonomous ceramic turbine rotor.
  • the one-piece turbine impeller consisting of impeller and shaft part, is mounted in two separate bearings from the adjacent rotating components and is only connected to it by torque-transmitting shafts.
  • the torque is positively introduced into the intermediate shaft, the positive engagement preferably being a polygonal profile.
  • the axial thrust of the turbine rotor is transmitted either to the compressor rotor or, via helical gears, to the bearing of the slowly rotating output shaft.
  • the disadvantage of this construction is that the separate, double mounting of the turbine rotor takes up a lot of installation space and the double mounting is cost-intensive and the connection area can only transmit torques.
  • the object of the invention is one for high speeds of at least 15,000 rpm. preferably to specify more than 20,000 rpm suitable and a one-piece gear element-heavy-duty pinion shaft for a geared turbocompressor, which is structurally optimal and inexpensive to manufacture the stress with regard to temperature and the type of medium to be conveyed.
  • the optimal adaptation to the stress occurring in the respective area of the pinion shaft is achieved in such a way that the shaft part, at the free end of which the impeller is detachably arranged, is designed as a separate part and is connected to the gear element.
  • the material for the shaft part is chosen so that it meets the stresses that occur.
  • a low-temperature resistant steel would be used for the shaft part.
  • the shaft part would be made from a high-temperature steel. When compressing gases that are mixed with acids, it makes sense to use a particularly corrosion-resistant material for the shaft part.
  • the advantage of the proposed composite technology can be seen in the fact that the gear element is still made of a known surface hardenable heat-treatable steel and a material that meets the stress is selected for the shaft part that comes into direct contact with the medium to be conveyed, including the impeller arranged on it.
  • the gear element and the entire gear part can continue to be made small, and the shaft part connected to it can also be optimally designed, since there is no restriction with regard to gear technology considerations with regard to the choice of material.
  • Another variant consists in providing both ends of the shaft part with a Hirth connection and the adjoining regions of the gearwheel element and the impeller also with a complementary Hirth toothing.
  • an expansion screw extending through the impeller and the shaft part is anchored in the gear element.
  • the gearwheel element has a threaded bore in the end region, into which the expansion screw can engage.
  • the other free end of the expansion screw also has a threaded section so that a nut that can be screwed onto it can clamp the impeller and the shaft part against the gear element.
  • the proposed arrangement has the disadvantage that the expansion screw in the case of an LNG compressor must also be made of a low-temperature-resistant steel and, because of the lower strength, can only transmit a lower tightening torque.
  • the Hirth connection must be made ready for installation on both sides, which can lead to angular deviations in the axis position if the manufacturing tolerances are taken into account.
  • the expansion screw is also proposed to be further developed.
  • This arrangement has the advantage that the expansion screw connecting the elements shaft part and gear element can be manufactured from a high-strength tempering steel, since this area does not come into contact with the frozen gas.
  • Another advantage is that after connecting the shaft part and gear element Hirth connection between impeller and shaft part can be ground in appropriately. An addition of manufacturing tolerances of the two Hirth connections with regard to shape and position tolerances is excluded.
  • FIG. 1 an embodiment of the pinion shaft according to the invention is shown in a longitudinal section.
  • the shaft part 16 has a Hirth toothing at both ends 17, 18.
  • the end region 19 of the shaft piece 25 of the gear element 20 and the end region 21 of the impeller 22 are of comparable design, so that the Hirth toothing can engage with one another.
  • an expansion screw 23 engages through a bore in the impeller 22 and the shaft part 16.
  • the right-hand threaded section 24 of the expansion screw 23 can be screwed into a threaded bore arranged in the shaft piece 25.
  • the left-hand threaded section 26 of the expansion screw 23 projects beyond the Front region 27 of the impeller 22. By means of one on this end region 27 of the impeller 22.
  • the parts 16, 20, 23 are braced against one another by means of a nut 28 which can be screwed onto this threaded section 26.
  • FIG. 2 shows a similar arrangement as Figure 1, but with a split expansion screw. To simplify matters, the same reference numerals have been used for the same parts.
  • the expansion screw connecting the shaft part 16, impeller 22 and gear element 20 is divided.
  • the one expansion screw 30 made from a conventional tempering steel extends from the gear element 20 via the right-hand Hirth toothing 18 to the shaft part 16.
  • An insulating element 32 for example made of PTFE, is located between the two expansion screws 30, 31.
  • the tension nut 33 connecting the two expansion screws 30, 31 to one another is only indicated here. The advantages which result from this arrangement have already been pointed out in the description, so that there is no need to repeat them here.
  • arrows 12 and 13 in impeller 22 indicate the direction of flow of the medium to be compressed.
  • the descending arrow 14 is intended to indicate that, in particular when the vehicle is at a standstill and during the start-up phase, when the medium to be conveyed has not experienced any or only a slight increase in temperature, the medium to be conveyed can also get into the shaft part.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (7)

  1. Turbomachine de transmission ayant un arbre de pignon comportant un élément de roue dentée (20) réalisé en une seule pièce et fabriqué à partir d'un acier d'amélioration pouvant être durci en surface, dont la zone de raccordement se convertissant en un arbre (25) est réalisée comme point d'appui, et une partie d'arbre (16) s'y raccordant, réalisée comme pièce séparée, et présentant un perçage, à l'extrémité libre de laquelle peut être agencé un rotor (22),
    caractérisée en ce que la turbomachine de transmission est réalisée comme turbocompresseur et en ce que la partie d'arbre (16) est reliée à la zone d'arbre (25) de l'élément de roue dentée (20) par l'intermédiaire d'une vis à extension (23), et la partie d'arbre (16) présente, aux deux extrémités, une denture Hirth (17,18) connue en soi, qui s'engage dans des dentures Hirth correspondantes des zones d'extrémité (19,21) de la zone d'arbre (25) de l'élément de roue dentée (20) et du rotor radial (22) relié de façon amovible à la partie d'arbre (16) sous forme d'un montage volant, la matière utilisée pour la partie d'arbre (16) étant adaptée à la sollicitation existante relativement à la température et au type du fluide à comprimer.
  2. Turbomachine de transmission selon la revendication 1,
    caractérisée en ce que la partie d'arbre (5,16) est constituée d'une matière résistant à de basses températures.
  3. Turbomachine de transmission selon la revendication 1,
    caractérisée en ce que la partie d'arbre (5,16) est constituée d'une matière résistant à des températures élevées.
  4. Turbomachine de transmission selon la revendication 1,
    caractérisée en ce que la partie d'arbre (5,16) est constituée d'une matière particulièrement résistante à la corrosion.
  5. Turbomachine de transmission selon les revendications 1 à 4,
    caractérisée en ce que la partie d'arbre (5) présente un perçage, à travers lequel s'engage une vis à extension (23) reliant la partie d'arbre (5) et la zone d'arbre (3,25) de l'élément de roue dentée (1,20).
  6. Turbomachine de transmission selon les revendications 1 à 4,
    caractérisée en ce que la vis à extension (23) s'étendant à travers le rotor radial (22) et la partie d'arbre (16) et présentant deux tronçons filetés (24,26) est ancrée dans la zone d'arbre (25) de l'élément de roue dentée (20), et la partie d'arbre (16) et le rotor radial (22) peuvent être serrés contre la zone d'arbre (25) de l'élément de roue dentée (20) au moyen d'un écrou (28) pouvant être vissé sur le côté (27) du rotor radial sur la partie filetée (26) de la vis à extension.
  7. Turbomachine de transmission selon la revendication 6,
    caractérisée en ce que la vis à extension est subdivisée (30,31) et une vis (30) s'étend de l'élément de roue dentée (20) jusque dans la partie d'arbre (16) et l'autre (31) de la partie d'arbre (16) jusqu'à la zone frontale (27) du rotor (22), et le serrage de la partie d'arbre (16) contre l'élément de roue dentée (20) est effectué par un écrou de traction (33) qui est en engagement avec les deux tronçons filetés, opposés l'un à l'autre, des deux vis à extension (30,31) et dont le diamètre externe est quelque peu plus petit que la diamètre interne de la partie d'arbre (16).
EP93250128A 1992-06-17 1993-05-06 Turbomachine Expired - Lifetime EP0575017B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4220127A DE4220127C1 (fr) 1992-06-17 1992-06-17
DE4220127 1992-06-17

Publications (2)

Publication Number Publication Date
EP0575017A1 EP0575017A1 (fr) 1993-12-22
EP0575017B1 true EP0575017B1 (fr) 1997-06-18

Family

ID=6461399

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93250128A Expired - Lifetime EP0575017B1 (fr) 1992-06-17 1993-05-06 Turbomachine

Country Status (3)

Country Link
EP (1) EP0575017B1 (fr)
DE (2) DE4220127C1 (fr)
NO (1) NO305260B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19627346C1 (de) * 1996-07-01 1997-11-20 Mannesmann Ag Vorrichtung zur lösbaren Befestigung eines Laufrades an einer Turbomaschine
DE10156228B4 (de) * 2001-11-15 2015-02-19 Atlas Copco Energas Gmbh Rotor einer Expansionsturbine für Tieftemperaturanwendungen
DE102009015862A1 (de) 2009-04-01 2010-10-07 Siemens Aktiengesellschaft Getriebeverdichterrotor für Kaltgasanwendungen
DE102010040288A1 (de) * 2010-09-06 2012-03-08 Siemens Aktiengesellschaft Rotor

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE892402C (de) * 1940-04-14 1953-10-08 Messerschmitt Boelkow Blohm Lagerung fuer Gasturbinenlaeufer mit Waermeschutz
CH288842A (de) * 1951-02-13 1953-02-15 Sulzer Ag Gasturbine für Arbeitsmittel hoher Temperatur.
GB866710A (en) * 1956-09-06 1961-04-26 Birmingham Small Arms Co Ltd Improvements in or relating to elastic-fluid turbines
DE1199055B (de) * 1961-03-03 1965-08-19 Austin Motor Co Ltd Laeufer fuer Stroemungsmaschinen
AT288102B (de) * 1968-07-24 1971-02-25 Man Turbo Gmbh Vorrichtung zur Übertragung des Drehmomentes zwischen einem Turbinenrotor und einem Getriebe
US3874824A (en) * 1973-10-01 1975-04-01 Avco Corp Turbomachine rotor assembly
DE2436270A1 (de) * 1974-07-27 1976-02-05 Motoren Turbinen Union Wellenverbindung
DE2510287A1 (de) * 1975-03-08 1976-09-16 Motoren Turbinen Union Gasturbine mit autonomen keramikturbinenlaeufer
DE2559172C2 (de) * 1975-12-30 1985-07-25 United Turbine AB & Co. Kommanditbolag, Malmö Gasturbinenanlage
US4934138A (en) * 1988-12-06 1990-06-19 Allied-Signal Inc. High temperature turbine engine structure

Also Published As

Publication number Publication date
DE4220127C1 (fr) 1993-09-16
NO305260B1 (no) 1999-04-26
DE59306767D1 (de) 1997-07-24
NO931605D0 (no) 1993-05-03
NO931605L (no) 1993-12-20
EP0575017A1 (fr) 1993-12-22

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