EP3054089A1 - Rotor creux d'une turbomachine avec bouclier thermique - Google Patents

Rotor creux d'une turbomachine avec bouclier thermique Download PDF

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Publication number
EP3054089A1
EP3054089A1 EP15153993.9A EP15153993A EP3054089A1 EP 3054089 A1 EP3054089 A1 EP 3054089A1 EP 15153993 A EP15153993 A EP 15153993A EP 3054089 A1 EP3054089 A1 EP 3054089A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
turbomachine
hollow shaft
rotor
threads
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Withdrawn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
EP15153993.9A
Other languages
German (de)
English (en)
Inventor
Karsten Kolk
Peter Schröder
Vyacheslav Veitsman
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 EP15153993.9A priority Critical patent/EP3054089A1/fr
Publication of EP3054089A1 publication Critical patent/EP3054089A1/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Withdrawn legal-status Critical Current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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2260/208—Heat transfer, e.g. cooling using heat pipes
    • 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
    • F05D2260/231—Preventing heat transfer

Definitions

  • the present invention relates to an axially flow-through turbomachine with a rotor comprising a plurality of disk-shaped or drum-shaped rotor components and at least one extending through the rotor components tie rod which braces the rotor components axially against each other, wherein one of the rotor components is formed by a hollow shaft, which has an axial passage opening and on whose outer peripheral surface a rotor bearing is arranged.
  • turbomachines are known in the prior art in different configurations.
  • a turbomachine in the form of a stationary gas turbine whose rotor is composed of a plurality of disk-shaped or drum-shaped rotor components, which are clamped axially against each other via a tie rod.
  • Some of the rotor components include vanes of a compressor unit along their outer circumference, others the blades of a turbine unit of the gas turbine.
  • a hollow shaft is provided as a drum-shaped rotor component, on the outer circumferential surface of which a rotor bearing in the form of a sliding bearing is arranged.
  • the present invention provides an axially flow-through turbomachine of the aforementioned type, which is characterized in that the inner peripheral surface of the hollow shaft is at least partially covered with a tubular heat shield formed, and that between the inner peripheral surface of the heat shield and the Tie rod existing annular space defines a cooling air flow channel.
  • a region of the turbomachine such as a turbine unit, with optimum space utilization cooling air can be supplied.
  • the inner peripheral surface of the hollow shaft is at least partially covered with a tubular heat shield, whereby a proper operation of the turbomachine is ensured.
  • the heat shield is made of a metal sheet.
  • the heat shield can be inexpensively manufactured by deep drawing.
  • spacers are provided which are configured and arranged such that during normal operation of the turbomachine, a predetermined air gap between the heat shield and the inner peripheral surface of the hollow shaft remains, which defines an air insulation layer. Thanks to such spacers prevents the heat shield during operation of the turbomachine due to the centrifugal forces applied to the bearing shaft applies.
  • the spacers are integrally formed with the heat shield and provided in particular in the form of beads. Accordingly, a very cost-effective design is achieved with a few items.
  • the heat shield is provided according to an embodiment of the present invention in the region of its free ends with threads which are arranged on the hollow shaft and correspondingly formed threads in engagement.
  • the threads the heat shield can be integrally formed with the heat shield.
  • the heat shield can also be held using threaded Stülpringen on the hollow shaft, which are arranged with arranged on the hollow shaft and correspondingly formed threads engagement, wherein the Stülpringe, when screwed with the provided on the hollow shaft threads, axially against Press the free ends of the heat shield.
  • the through hole of the hollow shaft widens on both sides, in particular in a cone shape, wherein the heat shield is formed divided and mounted from both sides of the through hole.
  • the heat shield parts at their mutually facing end portions on each other radially overlapping joining areas, which can be pushed over each other during assembly of the heat shield, whereby a proper alignment of the heat shield parts to each other and a proper attachment of the heat shield parts is guaranteed to each other.
  • the figures show a part of an axially flow-through turbomachine 1 according to an embodiment of the present invention, which in the present case is a stationary gas turbine.
  • the turbomachine 1 comprises a rotor 2, which is composed of a multiplicity of disk-shaped or drum-shaped rotor components 3, 4 and 5, which are braced axially against one another via a tie rod 6 extending through the rotor components 3, 4 and 5.
  • the rotor components 3 carry on their outer circumference present not shown blades of a compressor unit of the turbomachine 1, while the rotor components 4 along their outer circumference also not shown blades of a turbine unit of the turbomachine 1 record.
  • the rotor component 5 arranged between the compressor unit and the turbine unit is formed by a hollow shaft which has an axial, conically widening on both sides through opening 7 and on the outer surface of a bearing seat 8 is formed, which serves to receive a rotor bearing, not shown here in detail, which is preferably a plain bearing.
  • the inner peripheral surface 9 of the hollow shaft 5 is largely clad with a tubular heat shield 10, wherein an existing between the heat shield 10 and the tie rod 6 annular space 11 defines a cooling air flow passage through which the turbine unit during normal operation of the turbomachine 1 in the direction of arrow 12 cooling air is supplied.
  • the heat shield 10 comprises two heat shield parts 13 and 14 which are each made of a deep-drawn sheet metal and are flared at one of their free ends, wherein the contours of the conical widening of the heat shield parts 13 and 14 substantially the contours of the conical widenings of the through hole. 7 the hollow shaft 5 correspond.
  • the heat shield parts 13 and 14 are each provided with radially overlapping in the intended mounted state joining portions 15 and 16 which define a connector, so that the said end portions of the heat shield parts 13 and 14 can be inserted axially into each other, as in FIG. 3 is shown.
  • heat shield parts 13 and 14 are present in one piece with the heat shield parts 13 and 14 in the form of beads, which protrude in the direction of the inner peripheral surface 9 of the hollow shaft 5.
  • the heat shield parts 13 and 14 are provided in the region of their free ends with threads 18 which are arranged on the hollow shaft 5 and correspondingly formed threads 19 in engagement.
  • the heat shield parts 13 and 14 starting from opposite sides in the passage opening 7 of the hollow shaft 5 is inserted, the joining regions 15 and 16 being pushed into one another, whereupon the threads 18 of the heat shield parts 13 and 14 are screwed to the threads 19 of the hollow shaft 5. Subsequently, the rotor components 3, 4 and 5 are pushed onto the tie rod 6 and then clamped axially against each other via this, in order in this way the in FIG. 1 to produce shown arrangement.
  • the above-described construction of the turbomachine 1 is particularly advantageous in that the heat shield 10 inserted into the hollow shaft 5 transfers heat from the cooling air routed through the annulus 11 during normal operation of the turbomachine 1 to the rotor bearing arranged on the outside of the hollow shaft 5 reduced, whereby an excessive increase in the oil temperature of the bearing oil and thus a coking of the oil can be effectively counteracted. In this way, premature wear of the rotor bearing is counteracted in a simple and inexpensive manner.
  • FIG. 10 shows an alternative embodiment of a heat shield 20 according to another embodiment of the present invention, which can be used in place of the heat shield 10.
  • the heat shield 20 differs only from the heat shield 10 in that the free ends of the heat shield members 21 and 22 are not provided with a thread 18. Instead, provided with corresponding threads 23 Stülpringe 24 are provided, which can be slipped over the free ends of the heat shield parts 21 and 22 and screwed to the threads 19 of the hollow shaft 5 to the heat shield parts 21 and 22 axially against each other and press on the hollow shaft. 5 to fix.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15153993.9A 2015-02-05 2015-02-05 Rotor creux d'une turbomachine avec bouclier thermique Withdrawn EP3054089A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15153993.9A EP3054089A1 (fr) 2015-02-05 2015-02-05 Rotor creux d'une turbomachine avec bouclier thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15153993.9A EP3054089A1 (fr) 2015-02-05 2015-02-05 Rotor creux d'une turbomachine avec bouclier thermique

Publications (1)

Publication Number Publication Date
EP3054089A1 true EP3054089A1 (fr) 2016-08-10

Family

ID=52446298

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15153993.9A Withdrawn EP3054089A1 (fr) 2015-02-05 2015-02-05 Rotor creux d'une turbomachine avec bouclier thermique

Country Status (1)

Country Link
EP (1) EP3054089A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021124357A1 (de) 2021-09-21 2023-03-23 MTU Aero Engines AG Hitzeschutzelement für eine Lagerkammer einer Gasturbine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791091A (en) * 1950-05-15 1957-05-07 Gen Motors Corp Power plant cooling and thrust balancing systems
US2804280A (en) * 1951-03-20 1957-08-27 Gen Motors Corp Turbine bearing lubrication system
US3637049A (en) * 1970-03-03 1972-01-25 Gen Electric Continuous, self-pumping lubrications system for splined shafts
US4031699A (en) * 1974-10-25 1977-06-28 Fuji Jukogyo Kabushiki Kaisha Port liner assembly
US5267397A (en) * 1991-06-27 1993-12-07 Allied-Signal Inc. Gas turbine engine module assembly
EP1013893A2 (fr) * 1998-12-22 2000-06-28 General Electric Company Evitement de la dilatation thermique différentielle des éléments d'un rotor de turbine
EP1233147A2 (fr) * 2001-02-14 2002-08-21 Hitachi, Ltd. Turbine à gaz avec dispositif de refroidissement
EP1970530A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor d'une turbomachine thermique et turbomachine thermique
EP2383440A1 (fr) 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Turbine incluant un système d'étanchéité à air avec clapet
EP2474707A2 (fr) * 2011-01-11 2012-07-11 United Technologies Corporation Protection thermique multifonction pour moteur de turbine à gaz

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791091A (en) * 1950-05-15 1957-05-07 Gen Motors Corp Power plant cooling and thrust balancing systems
US2804280A (en) * 1951-03-20 1957-08-27 Gen Motors Corp Turbine bearing lubrication system
US3637049A (en) * 1970-03-03 1972-01-25 Gen Electric Continuous, self-pumping lubrications system for splined shafts
US4031699A (en) * 1974-10-25 1977-06-28 Fuji Jukogyo Kabushiki Kaisha Port liner assembly
US5267397A (en) * 1991-06-27 1993-12-07 Allied-Signal Inc. Gas turbine engine module assembly
EP1013893A2 (fr) * 1998-12-22 2000-06-28 General Electric Company Evitement de la dilatation thermique différentielle des éléments d'un rotor de turbine
EP1233147A2 (fr) * 2001-02-14 2002-08-21 Hitachi, Ltd. Turbine à gaz avec dispositif de refroidissement
EP1970530A1 (fr) * 2007-03-12 2008-09-17 Siemens Aktiengesellschaft Rotor d'une turbomachine thermique et turbomachine thermique
EP2383440A1 (fr) 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Turbine incluant un système d'étanchéité à air avec clapet
EP2474707A2 (fr) * 2011-01-11 2012-07-11 United Technologies Corporation Protection thermique multifonction pour moteur de turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021124357A1 (de) 2021-09-21 2023-03-23 MTU Aero Engines AG Hitzeschutzelement für eine Lagerkammer einer Gasturbine
US11988106B2 (en) 2021-09-21 2024-05-21 MTU Aero Engines AG Heat-protection element for a bearing chamber of a gas turbine

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