EP1785587A1 - Rotor de turbomachine à refroidissement interne - Google Patents

Rotor de turbomachine à refroidissement interne Download PDF

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Publication number
EP1785587A1
EP1785587A1 EP05024742A EP05024742A EP1785587A1 EP 1785587 A1 EP1785587 A1 EP 1785587A1 EP 05024742 A EP05024742 A EP 05024742A EP 05024742 A EP05024742 A EP 05024742A EP 1785587 A1 EP1785587 A1 EP 1785587A1
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor shaft
cavity
fluid
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.)
Withdrawn
Application number
EP05024742A
Other languages
German (de)
English (en)
Inventor
Kai Dr. Wieghardt
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP05024742A priority Critical patent/EP1785587A1/fr
Publication of EP1785587A1 publication Critical patent/EP1785587A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/207—Heat transfer, e.g. cooling using a phase changing mass, e.g. heat absorbing by melting or boiling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties

Definitions

  • the invention relates to a rotor of a turbomachine, in particular a steam and / or gas turbine, with a rotor blade carrying a rotor blade.
  • the blades arranged on the rotor shaft of the rotor are subjected to a hot working gas which, for example in the case of a steam turbine, is steam.
  • the hot working gas flowing around the rotor causes a heat input into the rotor shaft of the rotor, on the one hand as a result of direct contact of the hot working gas with the rotor shaft and, on the other hand, due to heating of the rotor blades arranged on the rotor shaft.
  • the rotor shaft of a rotor In operation, the rotor shaft of a rotor is exposed to high centrifugal forces, which can lead to high tangential stresses and creep strains with increasing temperature of the rotor shaft.
  • it is basically known from the prior art to cool the rotor shaft of a rotor.
  • the previously proposed measures for cooling a rotor shaft measures are technically complex and / or inappropriate to effect such a cooling of the rotor shaft, as a result that a real performance and / or increase in life could be achieved.
  • the rotor shaft near at least one foot of a arranged on the rotor shaft Blade has a cavity which is connected via at least one passage channel with the rotor shaft side facing the end of a foot for cooling purposes.
  • the cavity is also connected to a cooling system, by means of which the cavity is supplied with a cooling medium.
  • the one with the EP-A 0 926 311 proposed rotor is extremely complicated in its constructive design, since the cavity formed in the rotor shaft is connected to a cooling system and on the other with one of the number of blades arranged on the rotor shaft corresponding number of passageways. In this respect, the production of such a trained rotor disadvantageous manufacturing technology consuming and not least costly. In addition, the stability of the rotor shaft is impaired due to the large number of feedthrough channels to be provided. Furthermore, not least the lack of effectiveness of the EP-A 0 926 311 proposed cooling device of disadvantage. Namely, there is mainly a cooling of the feet of the blades arranged on the rotor shaft instead.
  • the invention proposes a rotor of a turbomachine, in particular a steam and / or gas turbine, with a rotor blades carrying rotor blades, wherein the rotor shaft surrounding a to the rotor shaft Atmosphere completed cavity extending in the axial direction of the rotor shaft in a region thereof, which has an axial temperature gradient when using the rotor as intended, and wherein the cavity is filled with serving as a cooling medium fluid having a higher heat capacity than air.
  • the rotor shaft of the rotor according to the invention has a cavity, namely one which is closed to the atmosphere surrounding the rotor shaft.
  • "Completed" in the sense of the invention means that the interior of the cavity is not connected to any further supply or discharge bores and / or lines of a cooling system, as in the rotor according to the EP-A 0 926 311 the case is.
  • the cavity according to the rotor according to the invention rather represents a volume space which is filled with a fluid serving as a cooling medium, which always remains in the cavity, that is, an exchange of the fluid in the cavity with a separately arranged cooling system is not provided.
  • a pressure compensation device may be provided, as will be described below.
  • the peculiarity of the rotor according to the invention thus lies in the closed cavity formed in the rotor shaft, which is filled with a fluid serving as a cooling medium, which cools the hot regions of the rotor shaft surrounding the cavity.
  • the cooling of the rotor shaft takes place exclusively in that the cooling medium located in the closed cavity circulates within the cavity and not by the fact that an exchange of the cooling medium in the cavity would be provided by means of a standing in fluid communication with the cavity cooling system.
  • the rotor according to the invention thus proves to be particularly simple in its structural design, which allows both manufacturing technology and from a economic point of view, a comparatively simple production.
  • the cavity extends in the axial direction of the rotor shaft, specifically in a region which, when the rotor is used as intended, has an axial temperature gradient.
  • axial temperature gradients is meant the temperature gradient in the longitudinal direction of the rotor shaft, which results as a result of the hot working gas flowing past in the longitudinal direction on the rotor shaft.
  • the hot working gas is guided past in the longitudinal direction of the rotor shaft, wherein the working gas cools in the course of the pass on the rotor shaft.
  • the rotor shaft heats up more strongly in the region of the inlet of the hot working gas than in the region of the outlet of the working gas passed past the rotor shaft.
  • a temperature gradient in the longitudinal direction of the rotor shaft which can be referred to as an axial temperature gradient, arises between the inlet and outlet regions.
  • the hollow space formed according to the invention in the rotor shaft extends in the axial direction over preferably the entire section of the rotor shaft, which as a result of an intended use of the rotor falls under an axial temperature gradient.
  • the fluid in the cavity is heated radially outwardly as a result of the heat input into the rotor shaft, which causes the fluid to expand, that is, it reduces its density.
  • the fluid In the direction of the longitudinal axis of the rotor shaft, the fluid is radially heated differently on the outside due to the temperature gradient running in the axial direction, that is, it forms in accordance with the axially extending temperature gradient, a density gradient within the radially outer side located in the cavity fluid.
  • the axial temperature gradient that is, the temperature gradient and the resulting density difference in the axial direction of the radially outer side located in the cavity fluid creates a convection flow within the cavity. This convection flow has an automatic circulation of the located in the cavity Fluids result.
  • the cooling medium used according to the invention is a fluid which has a higher heat capacity than air.
  • a fluid is in particular a gas, for example hydrogen or a gas mixture in question.
  • a cooling medium but also a liquid or a liquid mixture can be used.
  • More generally, in particular, low-density compressible cooling media are advantageous, while having good heat transfer and / or capacity properties. Conceivable, therefore, is the use of a vaporous cooling medium, such as water vapor, which is present in the cold state in the liquid state and in the hot state in the gaseous phase.
  • the above-described embodiment of the rotor shaft of the rotor according to the invention causes an excellent cooling of the same.
  • the convection flow of the fluid located in the cavity of the rotor shaft takes place automatically due to the outer side of the voltage applied to the rotor shaft temperature gradient, which is why the cooling of the rotor shaft in an advantageous manner self-sufficient, that works without supply or discharge of a cooling medium.
  • the cooling integrated into the rotor shaft cools the rotor shaft on the outer peripheral side, which makes it possible to apply hotter working gases to the rotor, as known from the prior art.
  • the range of applications of the rotor according to the invention is thus extended compared to known from the prior art, conventional rotors, which brings with respect to the rotor according to the invention an increase in performance and / or life in an advantageous manner.
  • a displacement body is arranged in the form of internals within the cavity.
  • the internals arranged in the cavity of the rotor shaft are preferably mounted so as to be heat-movable. Any tensions of the fixtures in the cavity by uncontrolled thermal expansion can be counteracted.
  • the internals are preferably formed of a porous material, such as ceramic.
  • the internals are preferably tubular and self-supporting. They have at their respective ends via suitable radial openings, so as not to hinder the flow of fluid within the cavity.
  • the cavity is formed as a conduit system which has both radially and axially to the rotor shaft extending bores.
  • the cavity can be formed by a conduit system be having a plurality of radially extending bores near the outer surface of the rotor shaft. These radial holes are fluidly connected via a plurality of axially extending bores with one or more further radially extending bores, which are formed, for example, in the region of the rotor shaft axis. In this way, a closed conduit system, through which the fluid used as a cooling medium is forcibly guided.
  • the cavity has a pressure compensation device.
  • a pressure compensation device may be required in particular if the fluid used as the cooling medium has a different thermal expansion coefficient than the rotor shaft material.
  • Such a pressure compensation device can be designed according to the invention in two different ways. According to a first alternative, provision may be made to fluidly connect the cavity to the atmosphere surrounding the rotor shaft by means of an axial bore. In order to prevent the fluid in the cavity from being discharged uncontrollably via this axial bore to the atmosphere surrounding the rotor shaft, this is to close for the purpose of pressure equalization axial bore on the atmosphere side with a pressure-sensitive closure piston.
  • the axial bore provided for the purpose of pressure equalization is thus tightly sealed on the atmosphere side. If, as a result of the heating of the fluid arranged in the cavity, a critical increase in pressure within the cavity occurs, the closure piston occluding the axial bore opens, which effects a pressure equalization.
  • the closure piston can be arranged spring-loaded within the axial bore and thus act in the manner of a pressure relief valve.
  • a displacement body is in the form of internals within the cavity
  • the displacement body forming internals are hollow and provide a pressure compensation space available. If there is a critical overpressure in the cavity, fluid can flow into the hollow internals to lower the pressure. If the pressure within the cavity decreases again, the amount of fluid received by the internals can be returned to the cavity.
  • This embodiment of the pressure compensation device is preferred because it requires no axial bore for the fluidic connection of the cavity with the atmosphere surrounding the rotor shaft.
  • the rotor shaft has two cavities of the aforementioned type, which are separated from each other by means of a partition wall.
  • the formation of two cavities is particularly useful in a two-flow design of the rotor shaft.
  • FIG. 1 shows a schematic side view of a rotor 1 according to the invention.
  • the rotor 1 shown in FIG. 1 has a rotor shaft 2 which is rotatably mounted about the shaft axis 3.
  • the rotor shaft 2 carries in Fig. 1, not shown blades, wherein the rotor shaft 2 for the purpose of arrangement of the blades circumferential grooves 4 carries, of which in Fig. 1 by way of example two are shown.
  • the feet of the blades not shown in Fig. 1.
  • the blades and thus also the rotor shaft 2 are acted upon by a hot working gas, which is introduced via the inlet 5 in the rotor 1.
  • the hot working gas passing via the inlet 5 into the rotor 1 flows through the rotor 1 in the longitudinal direction 8 of the rotor shaft 2, with reference to the plane of the drawing according to FIG. 1 from right to left.
  • the flow path of the hot working gas is indicated in FIG. 1 by the reference numeral 7. After flowing through the rotor 1, the hot working gas leaves the rotor 1 at the outlet 6.
  • the rotor shaft heats 2.
  • the heating of the rotor shaft 2 in the region of the inlet 5 is greatest, whereas the heating of the rotor shaft 2 in the region of the outlet 6 is the lowest.
  • a temperature gradient arises between the inlet 5 on the one hand and the outlet 6 on the other hand.
  • the rotor shaft 2 is thus heated differently with respect to its longitudinal extent, so that, starting from the inlet 5 in the direction of the outlet 6, an axial temperature gradient is established.
  • the rotor shaft 2 has a cavity 9.
  • This cavity 9 is filled with a fluid serving as a cooling medium, which may be gaseous, for example.
  • a gaseous fluid in particular hydrogen comes into consideration.
  • the fluid located in the cavity 9 is heated at the radially outer boundary wall of the cavity 9, in dependence on the temperature input made in the rotor shaft 2. As a result of the heating, the fluid in the cavity 9 expands, which leads to a reduction in the density of the heated fluid quantity fractions. It turns due to the axial temperature gradient applied to the rotor shaft 2, there is a density difference in the fluid in the cavity 9, along the inner surface of the wall delimiting the cavity 9 to the atmosphere surrounding the rotor shaft 2. Due to the temperature gradient and the resulting difference in density in the fluid located in the cavity 9, a convection flow, that is to say a fluid flow 10, automatically sets in.
  • the fluid located in the hot region of the rotor shaft 2 expands, that is, it reduces its density and is transported by the high centrifugal acceleration to the shaft axis 3 and thereafter into colder regions of the shaft axis 2, in which heat sinks 15 are located.
  • the heat sink 15 which are in the embodiment of FIG. 1 frontally of the cavity 9, the fluid located in the cavity 9 cools, gaining in density and is transported along the cavity inner wall from the respective colder into the hotter areas, creating a automatic cooling circulation with cooling effect for the radially outer side wall of the cavity 9 is formed.
  • FIG. 2 shows a schematic side view of a rotor with a double-flow rotor shaft 2.
  • the rotor shaft 2 or the blades arranged on the rotor shaft 2 and not shown in FIG. 2 are charged with a hot working gas which passes via the inlet 5 in the rotor 1.
  • the hot working gas passing via the inlet 5 into the rotor 1 is divided into two partial flows, with a partial flow starting from the inlet 5 from right to left and a partial flow starting from the inlet 5 from left to right with reference to the plane of the drawing according to FIG ,
  • the hot working gas flowing through the rotor 1 leaves the same with reference to the plane of the drawing according to FIG. 2 both on the left and on the right side via the outlets 6.
  • this has two cavities 9, in which for the purpose the cooling of the rotor shaft 2 is in each case a fluid.
  • the two cavities 9 are separated from each other by a partition wall 17, which is why the left in the drawing plane of FIG. 2 cavity 9 for cooling the rotor shaft 2 in the left and the reference to the drawing plane of FIG. 2 right cavity 9 for cooling the rotor shaft 2 in the right area serves.
  • the cavities 9 formed in the rotor shaft 2 can be designed differently depending on the application, which shows the rotor shaft 2 shown in FIG. 2 by way of example.
  • left cavity 9 is formed as a conduit system 18.
  • This line system 18 is formed from radial bores 13 and axial bores 14, which provide a closed loop system for the fluid in the cavity 9.
  • the fluid in the cavity 9 is forcibly guided.
  • the mode of operation of the cooling also corresponds in this embodiment of the cavity 9 to that described above with reference to FIG. Again, the region 16 of the rotor shaft 2, which is subject to an axial temperature gradient, cooled.
  • the right in the drawing plane of FIG. 2 cavity 9 is formed for the purpose of illustrating the invention in a different way than the reference to the drawing plane of FIG. 2 left cavity 9.
  • the reference to the drawing plane of FIG. 2 right Cavity 9 corresponds in its embodiment to that cavity 9 of FIG. 1.
  • two internals 11 are arranged in the right cavity 9 of FIG. 2, which serve as a displacement body. In this way, the amount of fluid in the cavity 9 can be reduced, which helps reduce the centrifugal forces initiated by the fluid and acting on the rotor 1.
  • the internals 11 are made of a porous material and are preferably arranged by means of heat-movable bearings 12 within the cavity 9. As can be seen from Fig.
  • baffles 11 a kind of conduit system through which the fluid located in the cavity 9 passes.
  • the internals 11 may also be at least partially hollow and provide a volume space for the purpose of pressure equalization available. If the pressure within the cavity 9 rises above a critical level, the fluid in the cavity 9 at least partially flows into the pressure compensation volumes provided by the internals 11. In the case of a pressure reduction, the quantities of the fluid contained in the cavity 9 can then be returned to the cavity 9 back from the fittings 11.
  • the rotor 1 exemplified with reference to FIGS. 1 and 2 is distinguished by its simple and robust shape of the rotor shaft cooling by temperature compensation.
  • the cooling concept is completely internal, that is arranged within the rotor shaft 2.
  • the function of the cooling concept is guaranteed as soon as a temperature gradient is present.
  • the rotor according to the invention is characterized by its stable construction, because he lacks radial bores, such as these for cooling the feet of the arranged on the rotor shaft blades with the EP-A 0 926 311 be proposed. In this respect, the rotor 1 according to the invention is much less sensitive to notch effects.
  • the proposed with the rotor 1 according to the invention cooling concept causes an extremely effective cooling of the rotor shaft, which makes it possible to increase the steam conditions at a given shaft material or to reduce creep damage.
  • the stability of the shaft relevant for the mechanical design can be increased by a factor of more than 2.
  • the range of applications for the rotor 1 according to the invention is increased, wherein the rotor 1 according to the invention can be used for all types of steam turbines.
  • the heat flow removed for cooling in the inflow becomes fed back to the steam in the further expansion process. The same applies to friction losses from the circulation of the fluid.
  • suitable internals 11 torsional vibrations can be damped in an advantageous manner.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05024742A 2005-11-11 2005-11-11 Rotor de turbomachine à refroidissement interne Withdrawn EP1785587A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05024742A EP1785587A1 (fr) 2005-11-11 2005-11-11 Rotor de turbomachine à refroidissement interne

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05024742A EP1785587A1 (fr) 2005-11-11 2005-11-11 Rotor de turbomachine à refroidissement interne

Publications (1)

Publication Number Publication Date
EP1785587A1 true EP1785587A1 (fr) 2007-05-16

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EP05024742A Withdrawn EP1785587A1 (fr) 2005-11-11 2005-11-11 Rotor de turbomachine à refroidissement interne

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EP (1) EP1785587A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2045442A1 (fr) * 2007-10-02 2009-04-08 Siemens Aktiengesellschaft Agencement doté d'une source de chaleur, d'un dissipateur thermique et d'un arbre rotatif
WO2017200828A1 (fr) * 2016-05-20 2017-11-23 Borgwarner Inc. Arbre de rotor de turbocompresseur rempli creux

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL80867C (fr) * 1900-01-01
DE333211C (de) * 1919-08-06 1921-02-19 Bbc Brown Boveri & Cie Verfahren und Einrichtung bei Dampf- oder Gasturbinen mit Vorwaerts- und Rueckwaertsbeschauflung auf einer Laufradtrommel zur Nutzbarmachung der von der leerlaufenden Beschauflung erzeugten Waerme
FR897710A (fr) * 1942-06-04 1945-03-29 Rotor refroidi de turbine à gaz
GB628228A (en) * 1946-09-24 1949-08-24 Bbc Brown Boveri & Cie Cooled rotors
DE863391C (de) * 1941-09-10 1953-01-15 Daimler Benz Ag Kuehlung von mit einem heissen Arbeitsmittel beaufschlagten, aus Leichtmetall hergestellten Laeufern fuer schnell laufende, zur Verdichtung gasfoermiger Mittel dienende Stroemungsmaschinen
DE865839C (de) * 1944-03-22 1953-02-05 Ernst Dr-Ing Schmidt Betriebsverfahren fuer Gasturbine
US2635805A (en) * 1946-09-24 1953-04-21 Bbc Brown Boveri & Cie Turbine with cooled rotor
FR1117699A (fr) * 1954-02-18 1956-05-25 Parsons & Marine Eng Turbine Dispositif de refroidissement des aubes et du rotor de turbines à gaz
DE1038839B (de) * 1957-06-07 1958-09-11 Basf Ag Anordnung zum Betrieb von Gasturbinen mit Verdampfungskuehlung des Laeufers
US3842596A (en) * 1970-07-10 1974-10-22 V Gray Methods and apparatus for heat transfer in rotating bodies
EP0500972A1 (fr) * 1991-02-25 1992-09-02 Asea Brown Boveri Ag Rotor de turbomachine
EP0926311A1 (fr) 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor pour une turbomachine
US5954478A (en) * 1996-09-10 1999-09-21 Aerodyne Research, Inc. Evaporatively cooled rotor for a gas turbine engine

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL80867C (fr) * 1900-01-01
DE333211C (de) * 1919-08-06 1921-02-19 Bbc Brown Boveri & Cie Verfahren und Einrichtung bei Dampf- oder Gasturbinen mit Vorwaerts- und Rueckwaertsbeschauflung auf einer Laufradtrommel zur Nutzbarmachung der von der leerlaufenden Beschauflung erzeugten Waerme
DE863391C (de) * 1941-09-10 1953-01-15 Daimler Benz Ag Kuehlung von mit einem heissen Arbeitsmittel beaufschlagten, aus Leichtmetall hergestellten Laeufern fuer schnell laufende, zur Verdichtung gasfoermiger Mittel dienende Stroemungsmaschinen
FR897710A (fr) * 1942-06-04 1945-03-29 Rotor refroidi de turbine à gaz
DE865839C (de) * 1944-03-22 1953-02-05 Ernst Dr-Ing Schmidt Betriebsverfahren fuer Gasturbine
US2635805A (en) * 1946-09-24 1953-04-21 Bbc Brown Boveri & Cie Turbine with cooled rotor
GB628228A (en) * 1946-09-24 1949-08-24 Bbc Brown Boveri & Cie Cooled rotors
FR1117699A (fr) * 1954-02-18 1956-05-25 Parsons & Marine Eng Turbine Dispositif de refroidissement des aubes et du rotor de turbines à gaz
DE1038839B (de) * 1957-06-07 1958-09-11 Basf Ag Anordnung zum Betrieb von Gasturbinen mit Verdampfungskuehlung des Laeufers
US3842596A (en) * 1970-07-10 1974-10-22 V Gray Methods and apparatus for heat transfer in rotating bodies
EP0500972A1 (fr) * 1991-02-25 1992-09-02 Asea Brown Boveri Ag Rotor de turbomachine
US5954478A (en) * 1996-09-10 1999-09-21 Aerodyne Research, Inc. Evaporatively cooled rotor for a gas turbine engine
EP0926311A1 (fr) 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor pour une turbomachine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2045442A1 (fr) * 2007-10-02 2009-04-08 Siemens Aktiengesellschaft Agencement doté d'une source de chaleur, d'un dissipateur thermique et d'un arbre rotatif
WO2017200828A1 (fr) * 2016-05-20 2017-11-23 Borgwarner Inc. Arbre de rotor de turbocompresseur rempli creux
US10041400B2 (en) 2016-05-20 2018-08-07 Borgwarner Inc. Hollow filled turbocharger rotor shaft

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