EP0575017A1 - Arbre liant une roue dentée à la roue d'une turbomachine - Google Patents

Arbre liant une roue dentée à la roue d'une turbomachine Download PDF

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Publication number
EP0575017A1
EP0575017A1 EP93250128A EP93250128A EP0575017A1 EP 0575017 A1 EP0575017 A1 EP 0575017A1 EP 93250128 A EP93250128 A EP 93250128A EP 93250128 A EP93250128 A EP 93250128A EP 0575017 A1 EP0575017 A1 EP 0575017A1
Authority
EP
European Patent Office
Prior art keywords
shaft
shaft part
gear element
impeller
pinion
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.)
Granted
Application number
EP93250128A
Other languages
German (de)
English (en)
Other versions
EP0575017B1 (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 pinion shaft for a transmission turbomachine according to the preamble of claim 1.
  • the gearwheel element is usually made of an alloyed tempering steel with a view to sufficient fatigue strength and flank strength, 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, in particular during standstill and in the start-up phase, part of the wave range is also exposed to the frozen gas.
  • both the impeller and the subsequent shaft part could be made in one piece from a low-temperature-resistant steel.
  • the production requires a great deal of machining, since the external dimensions of the impeller determine the size of the block to be machined.
  • the object of the invention is a for high speeds of at least 15,000 rpm. preferably more than 20,000 rpm. Specify suitable and a one-piece gear element having heavy-duty pinion shaft for a geared turbo machine, which is structurally optimal and inexpensive to manufacture adapted to 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 from a known surface-hardening 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 still be made small, and the shaft part connected with it can also be optimally designed, since no restrictions with regard to gear technology considerations are required 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 heat-treatable 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 the impeller and shaft part can be ground appropriately. An addition of manufacturing tolerances of the two Hirth connections with regard to shape and position tolerances is excluded.
  • FIG. 1 shows a sketch of a first embodiment of the pinion shaft according to the invention, for example a gear compressor, in a longitudinal section. It consists of a gear element 1 which has a toothing 2 which meshes with a gear of the transmission (not shown here). This is followed by a shaft piece 3, which is designed as a bearing 4.
  • the shaft part 5 made of another material is connected to the gear element 1, for example, by means of a shrink connection. So that large moments of force can also be transmitted, it is known to design the end region 6 of the shaft part 5 as a polygon. In such a case, the end region 7 of the shaft piece 3 comprising this region 6 would also be an inner polygon designed to be complementary thereto exhibit.
  • the impeller 8 is connected to the shaft part 5 via a conical seat 9, which is only indicated here.
  • the tension required for a secure fit is generated by the nut 11 screwed onto the threaded part 10 of the shaft part 5.
  • the direction of flow of the medium to be compressed is indicated by the arrows 12, 13 in the impeller 8.
  • the arrows 12, 13 have an opposite direction.
  • the descending arrow 14 is intended to indicate that, particularly when the vehicle is at a standstill and during the start-up phase, if the medium to be conveyed has not experienced any or only a slight increase in temperature, the medium to be conveyed can also reach the shaft part 5.
  • the separately manufactured gear element 1, on the other hand, can be produced in a known manner from a heat-treatable steel that is optimized with regard to the transmission technology requirements.
  • FIG. 2 shows a second embodiment of the pinion shaft according to the invention in a comparable longitudinal section, the same reference numerals being used for the same parts.
  • the shaft part 16 has Hirth teeth 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.
  • 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. 3 shows a similar arrangement as Figure 2, but with a split expansion screw.
  • the expansion screw connecting the shaft part 16, impeller 22 and gear element 20 is divided.
  • the one expansion screw 30 made of a conventional tempering steel extends from the gear element 20 over the right-hand Hirth toothing 18 to the shaft part 16.
  • the second expansion screw 31, which is also made of cold-tough steel in the case of an LNG compressor extends from the shaft part 16 over the left-hand Hirth toothing 17 into the front area 27 of the impeller 22.
  • 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP93250128A 1992-06-17 1993-05-06 Turbomachine Expired - Lifetime EP0575017B1 (fr)

Applications Claiming Priority (2)

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

Publications (2)

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

Cited By (2)

* 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
FR2832177A1 (fr) * 2001-11-15 2003-05-16 Atlas Copco Energas Rotor de turbine d'expansion

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009015862A1 (de) 2009-04-01 2010-10-07 Siemens Aktiengesellschaft Getriebeverdichterrotor für Kaltgasanwendungen
DE102010040288A1 (de) * 2010-09-06 2012-03-08 Siemens Aktiengesellschaft Rotor

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH288842A (de) * 1951-02-13 1953-02-15 Sulzer Ag Gasturbine für Arbeitsmittel hoher Temperatur.
DE892402C (de) * 1940-04-14 1953-10-08 Messerschmitt Boelkow Blohm Lagerung fuer Gasturbinenlaeufer mit Waermeschutz
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
DE1935268A1 (de) * 1968-07-24 1970-04-16 Man Turbo Gmbh Vorrichtung und Verfahren zum Herstellen der Vorrichtung zur UEbertragung des Drehmomentes zwischen einem Turbinenrotor und einem Getriebe
US3874824A (en) * 1973-10-01 1975-04-01 Avco Corp Turbomachine rotor assembly
FR2279972A1 (fr) * 1974-07-27 1976-02-20 Motoren Turbinen Union Dispositif de liaison entre des arbres
DE2510287A1 (de) * 1975-03-08 1976-09-16 Motoren Turbinen Union Gasturbine mit autonomen keramikturbinenlaeufer
DE2559172A1 (de) * 1975-12-30 1977-07-14 United Turbine Ab & Co Gasturbinenanlage
WO1990006420A1 (fr) * 1988-12-06 1990-06-14 Allied-Signal Inc. Structure de moteur a turbine a haute temperature

Patent Citations (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
DE1935268A1 (de) * 1968-07-24 1970-04-16 Man Turbo Gmbh Vorrichtung und Verfahren zum Herstellen der Vorrichtung zur UEbertragung des Drehmomentes zwischen einem Turbinenrotor und einem Getriebe
US3874824A (en) * 1973-10-01 1975-04-01 Avco Corp Turbomachine rotor assembly
FR2279972A1 (fr) * 1974-07-27 1976-02-20 Motoren Turbinen Union Dispositif de liaison entre des arbres
DE2510287A1 (de) * 1975-03-08 1976-09-16 Motoren Turbinen Union Gasturbine mit autonomen keramikturbinenlaeufer
DE2559172A1 (de) * 1975-12-30 1977-07-14 United Turbine Ab & Co Gasturbinenanlage
WO1990006420A1 (fr) * 1988-12-06 1990-06-14 Allied-Signal Inc. Structure de moteur a turbine a haute temperature

Cited By (2)

* 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
FR2832177A1 (fr) * 2001-11-15 2003-05-16 Atlas Copco Energas Rotor de turbine d'expansion

Also Published As

Publication number Publication date
EP0575017B1 (fr) 1997-06-18
DE4220127C1 (fr) 1993-09-16
NO931605D0 (no) 1993-05-03
DE59306767D1 (de) 1997-07-24
NO305260B1 (no) 1999-04-26
NO931605L (no) 1993-12-20

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