EP1867839A1 - Roue de turbine de turbomachine et procédé d'assemblage associé - Google Patents

Roue de turbine de turbomachine et procédé d'assemblage associé Download PDF

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Publication number
EP1867839A1
EP1867839A1 EP06012298A EP06012298A EP1867839A1 EP 1867839 A1 EP1867839 A1 EP 1867839A1 EP 06012298 A EP06012298 A EP 06012298A EP 06012298 A EP06012298 A EP 06012298A EP 1867839 A1 EP1867839 A1 EP 1867839A1
Authority
EP
European Patent Office
Prior art keywords
impeller
blade root
blade
turbine wheel
mounting groove
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Withdrawn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
EP06012298A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Michael Dankert
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 EP06012298A priority Critical patent/EP1867839A1/fr
Publication of EP1867839A1 publication Critical patent/EP1867839A1/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Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses

Definitions

  • the invention relates to a turbine wheel for a turbomachine with an impeller and a blade.
  • the invention further relates to a method for mounting a turbine wheel for a turbomachine.
  • a flow medium is transported in a flow channel or energy is obtained from a flowing flow medium.
  • blades are arranged in the flow channel.
  • the vanes are mounted to a vane support forming a confining wall of the hot gas duct.
  • the vanes suitably direct the flow medium onto the blades, which are connected to a rotor and rotated so that kinetic energy of the flow medium is converted to rotational energy.
  • the EP 1 058 772 B1 shows a turbine blade mounting with locally bulging areas, which extend in the vicinity of the lower contact planes of the blade root with the running disk axially away from the disk surface.
  • the disadvantage is that the rotation system is added by the bulging areas of mass.
  • the turbine fretting occurs at the contact surfaces of blade root and impeller.
  • FIG. 12 shows rounded or convex surfaces of the mounting groove in the impeller and the blade root, whereby stresses on the groove or mecaniclijnszähnen be removed and distributed to shallower areas of the groove or the foot. Due to the design, a positive engagement of the long teeth of the teeth through the groove longitudinal teeth is not possible in all loading phases of the turbine wheel, which causes fretting wear, especially during load changes, at the contact surfaces of the groove and foot.
  • the object of the invention is the disclosure of a turbine wheel for a turbomachine, which has a particularly high mechanical strength, in particular with regard to long-term effects.
  • Another object of the invention is the disclosure of a method for mounting a turbine wheel for a Turbomachine, which leads to a mounting with a particularly high mechanical strength, especially with regard to long-term effects.
  • a turbine wheel for a turbomachine comprising an impeller having a peripheral surface which has a fastening groove, and comprising a blade having a blade root, wherein the blade is fastened to the peripheral surface of the impeller, wherein the blade root engages the attachment groove, the blade root being fitted with a transition fit or press fit into the attachment groove.
  • the ISO tolerance system includes a basic tolerance system, which includes the size of the tolerances, and a basic dimensioning system, which determines the position of the tolerances for external and internal dimensions.
  • Another positive effect of the selected fitting system relates to corrosion on the surfaces of the blade root and the fastening groove as a result of the hot gas flowing through the gaps between the blade root and the fastening groove during clearance.
  • the tightness achieved by the interference or interference fit makes a special coating of the surfaces superfluous to protect against corrosion.
  • the blade root and the fastening groove are configured such that at least 90% of the blade root surface facing the fastening groove bears against this fastening groove.
  • the design of the blade root is not fixed to a particular shape, such as Christmas tree profile, dovetail or hammer head profile. The larger the contact area, the stronger the desired improvements, such as more positive force transmission, more homogeneous load and less corrosion, resulting in longer service life.
  • the preferred fit is therefore a press fit with 100% contact between blade root surface and mounting groove.
  • a preferred embodiment of the invention has an axial orientation of the mounting groove in the impeller.
  • the Mounting groove is designed as a circumferential groove, the installation can be done faster in the axial variant, so that the necessary for the installation temperature difference between the blade root and impeller can be chosen as low as possible, which is reflected positively in the effort.
  • the impeller and blade materials have the same LCF values, which are the same cyclic fatigue properties. Further preferably, the service lives of the impeller and blade are about the same as, e.g. at the last compressor or turbine stage. Although a blade replacement with built-in turbine by local cooling or heating is possible, in practice, the turbine wheel must be removed.
  • the object directed to a method is achieved according to the invention by a method for mounting a turbine wheel for a turbomachine, comprising an impeller having a peripheral surface having a mounting groove, and comprising a blade with a blade root, wherein a blade and the impeller of a turbine wheel, directly before they are put together, be brought to different temperatures.
  • the invention takes advantage of the effect that most materials expand when heated and contract on cooling.
  • the blade root is specifically provided with an oversize, so that at a reference temperature of blade root and mounting groove installation is not possible.
  • the blade is cooled prior to installation in the impeller. Changing the temperature of the smaller component requires the least amount of mechanical and energy expenditure and can be done most quickly.
  • the impeller is heated prior to installation of the blade.
  • the advantage of this method over the Cooling is that no condensation, as on the cooled blade foot without protective atmosphere, can form. More preferably, prior to installation of the blade into the impeller, the blade is cooled and the impeller is heated. The combination of both methods is particularly advantageous for small blades or wheels, since the highest temperature difference of about 300 ° C to 400 ° C must be achieved in order to achieve the necessary thermal expansions or volume decreases.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 is directed along a turbine axis 10 and has a compressor 3, a combustion chamber 5 and a turbine part 7 successively along the turbine axis 10.
  • the compressor 3 and the turbine part 7 are arranged on a common turbine shaft 9.
  • a hot gas duct 12 is formed in the guide vanes 11 and blades 13, which are arranged on the turbine shaft 9, protrude into it.
  • ambient air 14 is sucked in by the compressor 3 and compressed to compressor air 15.
  • the compressor air 15 is burned with fuel in the combustion chamber 5 to hot gas 17, which flows through the hot gas channel 12. It puts it on the effect on the blades 13 the turbine shaft 9 in motion.
  • the rotational energy of the turbine shaft 9 can be used, for example, to generate electrical energy.
  • FIG. 2 shows a blade 31, comprising a blade root 32 with a Schaufelfußober Design 35, a blade platform 33, which forms the conclusion of the underlying blade root 32, and an airfoil 34. Furthermore, Figure 2 shows the detail of a view of an impeller 42 having a peripheral surface 43rd , Fastening grooves 44 and their surfaces 45.
  • FIG. 2 shows blade root 32 and impeller 42 prior to assembly at a reference temperature T R.
  • the blade root 32 has an oversize: d w (T R )> d B (T R ).
  • FIG. 3 shows a detail of a view of a turbine wheel 41 during the installation of the blade root 32 into the fastening groove 44 of a heated impeller 42.
  • the fastening groove 44 is widened due to the higher temperature T of the impeller 42 compared to the blade root 32: d W (T R ) ⁇ d B (T), T R ⁇ T.
  • the blade root 32 can be easily fitted in the fixing groove 44 (installation play).
  • Figure 4 shows a section of a view of a turbine wheel 41 after the blade root 32 has been fitted into the mounting groove 44 and blade root 32 and mounting groove 44 are already thermalized.
  • blade root 32 and mounting groove 44 are here thermalized to reference temperature T R and there is a interference fit with complete Contact between blade root surface 35 and mounting groove surface 45.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06012298A 2006-06-14 2006-06-14 Roue de turbine de turbomachine et procédé d'assemblage associé Withdrawn EP1867839A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06012298A EP1867839A1 (fr) 2006-06-14 2006-06-14 Roue de turbine de turbomachine et procédé d'assemblage associé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06012298A EP1867839A1 (fr) 2006-06-14 2006-06-14 Roue de turbine de turbomachine et procédé d'assemblage associé

Publications (1)

Publication Number Publication Date
EP1867839A1 true EP1867839A1 (fr) 2007-12-19

Family

ID=37110343

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06012298A Withdrawn EP1867839A1 (fr) 2006-06-14 2006-06-14 Roue de turbine de turbomachine et procédé d'assemblage associé

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Country Link
EP (1) EP1867839A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113833691A (zh) * 2020-06-08 2021-12-24 中国航发商用航空发动机有限责任公司 一种风扇组件及涡轮风扇发动机

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5872604A (ja) * 1981-10-26 1983-04-30 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
DE19619316A1 (de) * 1996-05-14 1997-11-20 Voith Hydro Gmbh Laufrad für eine Freistrahlturbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5872604A (ja) * 1981-10-26 1983-04-30 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
DE19619316A1 (de) * 1996-05-14 1997-11-20 Voith Hydro Gmbh Laufrad für eine Freistrahlturbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113833691A (zh) * 2020-06-08 2021-12-24 中国航发商用航空发动机有限责任公司 一种风扇组件及涡轮风扇发动机

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