EP1970528A1 - Rotor d'une turbomachine thermique - Google Patents

Rotor d'une turbomachine thermique Download PDF

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Publication number
EP1970528A1
EP1970528A1 EP07005083A EP07005083A EP1970528A1 EP 1970528 A1 EP1970528 A1 EP 1970528A1 EP 07005083 A EP07005083 A EP 07005083A EP 07005083 A EP07005083 A EP 07005083A EP 1970528 A1 EP1970528 A1 EP 1970528A1
Authority
EP
European Patent Office
Prior art keywords
rotor
tie rod
ring
ring segments
spring elements
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Withdrawn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
EP07005083A
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Armin Hülfenhaus
Andreas Lüttenberg
Raymond Slaughter
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP07005083A priority Critical patent/EP1970528A1/fr
Publication of EP1970528A1 publication Critical patent/EP1970528A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/10—Anti- vibration means

Definitions

  • the invention relates to a rotor of a thermal fluid machine with a number of individual, held together by a tie rod and assembled into a unit rotor parts.
  • the invention further relates to a thermal turbomachine with such a rotor.
  • the thermal turbomachinery includes steam and gas turbines as well as rotary compressors and jet engines. These usually have a rotatably mounted rotor surrounded by a stationary housing.
  • the fixed components of a thermal turbomachine are collectively referred to as a stator.
  • a flow channel extending in the axial direction of the turbomachine for a compressible flow medium is arranged.
  • On the rotor usually in the flow channel projecting and combined into groups of blades or rows of blades blades are attached.
  • the blades serve to drive the rotor shaft by momentum transfer from a hot and pressurized flow medium.
  • the thermal energy of the flow medium is thus converted in its relaxation in mechanical energy that can be used for example to drive an electric generator.
  • a compressor unit and a turbine unit are preferably arranged on a common shaft.
  • the compressor also called a compressor, draws in cold ambient air, compresses it and then feeds it to a combustion chamber where it is burned together with an injected fuel.
  • the hot combustion gases eventually flow under high pressure and at high speed into the turbine unit and drive them. Part of the mechanical energy thus generated is used to drive the compressor, the remaining part being available as usable energy.
  • the rotor of a gas turbine is also referred to as a rotor, which is exposed to a high mechanical and thermal stress. Mainly due to the high temperature of the working medium and the forces acting on the rotor forces during operation of the gas turbine, the rotor component is heavily stressed. Nevertheless, in order to be able to ensure operational safety on the one hand and to keep the manufacturing costs of the runner within acceptable limits on the other hand, a large number of design options have been proposed in the past.
  • a proposed embodiment of the rotor for example, by the production of a part feasible.
  • a production method is comparatively complicated in the manufacturing process.
  • no order-independent prefabrication and no parallel processing of individual parts is possible, resulting in high production throughput times.
  • a larger axial distance between the impeller discs must be accepted in order to work with the appropriate tools.
  • these production-related relatively large distances between the wheels worsen the rotor dynamics.
  • the rotor can also be composed of individual rotor parts.
  • the rotor parts of the rotor component are mounted on a shaft and optionally shrunk.
  • the individual rotor parts are held together via a tie rod.
  • the tie rod is guided by an axially extending recess in the rotor parts, whereby the rotor parts can be clamped together.
  • the rotor of the gas turbine is arranged at the end by suitable bearings in the housing of the turbine.
  • vibrations of the rotor component occur whose frequency u. a. from the distance between the two thrust bearings, d. H. is dependent on the free-swinging length of the rotor, in particular of the free-swinging length of the tie rod, in such a construction.
  • With increasing length of the gas turbine and the free-swinging length of the tie rod increases, which causes its natural frequency shifts to a lower level near the rotational frequency of the rotor component. This frequency shift can lead to impermissibly high vibration amplitudes during operation of the gas turbine, which impair the function of the rotor and can lead to damage to the turbine.
  • the invention is therefore based on the object to provide a rotor of the type mentioned, which ensures safe operation of the gas turbine even with increasing overall length.
  • the vibration amplitudes of the tie rod be kept as small as possible, especially in the area of the central hollow shaft.
  • the tie rod with a number of, a tie rod surrounding the ring forming ring segments is provided, wherein the ring segments are clamped in the axially extending recess of the rotor by means of tangentially acting and circumferentially arranged between the ring segments spring elements and wherein the Tie rod is fixed within the ring segments by radially acting and seen in the circumferential direction of the tie rod symmetrically arranged spring elements.
  • the invention is based on the consideration that just for the achievement of an effective damping of the oscillations of the tie rod this should be suitably supported in the rotor, the thermally induced different expansions of the rotor components should still be compensated.
  • the fact should be taken into account that due to the increasing requirements with respect to the performance of the turbine whose length increases, whereby the natural frequency of the tie rod approaches the operating speed of the gas turbine.
  • the tie rod should be suitably supported for this purpose to increase its rigidity. This is achieved in that the tie rod is supported in at least one rotor part by means of a number of preferably symmetrically distributed around the tie rod and radially acting spring elements is supported.
  • ring segments are provided as support elements. These form together with a front between each two ring segments arranged spring element a surrounding the tie rod ring. Starting from these ring segments, the tie rod is fixed axially in the rotor part by means of the radially acting spring elements.
  • the front side between the individual ring segments are arranged Spring elements, acting spring elements.
  • suitable holding elements may be provided on the ring segment.
  • the spring elements used in this system have in addition to the above-mentioned functions, the task to dampen the oscillations of the tie rod occurring during operation of the gas turbine.
  • the tangentially acting spring elements can in principle be formed from different types of springs such as torsion springs or elastomer springs.
  • the use of disc springs is particularly preferred since these have a number of advantageous properties in comparison to other types of spring.
  • disc springs can absorb very large forces even in a small installation space, with their spring characteristic linear or degressive and can be switched by a suitable arrangement and progressively.
  • the characteristic of a spring element formed from a number of disc springs can be varied by the appropriate combination of the individual disc springs within wide limits.
  • this is surrounded by a retaining ring for transmitting the spring force on the tie rod.
  • the retaining ring is expediently non-positively and / or positively with connected to the tie rod. For example, this can be shrunk onto the tie rod.
  • This type of connection is particularly suitable, since thus a particularly rigid connection between the retaining ring and the tie rod is made possible in a simple manner.
  • the retaining ring is provided with a number of its surface protruding guide elements.
  • the shape of the guide elements preferably corresponds to a shape suitable for receiving the spring elements.
  • the spring elements can be fixed in the circumference of the rotor part, so that even during operation of the gas turbine whose position and orientation remains largely unchanged.
  • the guide elements are preferably an integral part of the retaining ring, wherein to avoid an imbalance, the guide elements should be arranged symmetrically in the circumference of the retaining ring.
  • the guide elements are arranged, for example, for receiving spirally curved or elastomeric spring elements, in particular for receiving disc springs, aligned radially on the retaining ring.
  • a guided spring element is achieved that the spring force can act radially on the retaining ring on the tie rod.
  • the expansion of the guide elements in the radial direction should not be too large to prevent a collision with the guide element opposite retaining ring.
  • this system for supporting the tie rod in the rotor part of the guide element opposite ring segment is provided with a profile corresponding to the respective guide element recess.
  • the recess is preferably introduced at a location of the axis of symmetry extending in the radial direction of the ring segment.
  • the ratio between the radial extent of the guide element and the depth of the recess in the ring segment is to be chosen taking into account the spring constant of the spring element so that a sufficiently large range of motion of the guide member is ensured in the recess, in particular during operation of the gas turbine.
  • the rotor part is a rotor disk or a hollow shaft. If the rotor part is designed as a rotor disk, it can also carry blades of the turbine or of the compressor on its outer circumference. In the event that the rotor part is formed as a arranged between the turbine section and the compressor section hollow shaft, the tie rod can be supported in the central region of its longitudinal extent on the hollow shaft.
  • the advantages achieved by the invention are, in particular, that a secure operation of the gas turbine is made possible with such an increasing length by such a support of the tie rod in the rotor part.
  • the damping of the vibrations of the tie rod occurring during operation of the gas turbine is thus made possible.
  • the thermally induced relative movements between the rotor parts and the tie rod can be compensated particularly well.
  • a cooling necessary due to the high thermal load of the rotor component is ensured by means of a cooling air duct extending in the axial direction of the rotor.
  • FIG. 1 A rotor 2 of a gas turbine with a number of individual, held together by a tie rod 4 and assembled into a unit rotor parts 6 is in FIG. 1 shown.
  • the respective rotor parts 6 are on the connection side provided with symmetrically to the central axis M of the rotor 2 extending recesses 8, wherein the resulting contours are formed corresponding to the contours of the respective adjacent rotor part 6, whereby a concentric alignment of the rotor part 6 to the central axis M is effected.
  • Each of the rotor parts 6 is provided for guiding the tie rod 4 with an axially extending bore 10, wherein the tie rod is screwed end to a rotor part 6 and thus all interposed rotor parts 6 are held together.
  • the introduced in the rotor parts 6 recesses 8 serve to guide a cooling medium for cooling the rotor components by cooling air is supplied via a cooling channel formed between the tie rod 4 and the rotor part 6.
  • the tie rod 4 is supported at least in one, preferably in the region of the central hollow shaft rotor part 6. Such a trained rotor part 6 is in FIG. 2 shown.
  • a retaining ring 12 extending from the surface extending in the radial direction guide elements 14.
  • the guide elements 14 are arranged symmetrically distributed on the circumference of the retaining ring 12, wherein the free ends are guided in a corresponding to the profile of the guide member 14 recess 16 in a radially opposite ring segment 18.
  • the radial spring elements 22 used for fixing the tie rod preferably all have the same spring constant, whereby the tie rod 4 is centered in the manner of a self-centering design without active measures in the rotor part 6.
  • each of the radial spring elements 22 is composed of five disc springs 20, wherein the disc springs 20 are connected in series.
  • the case surrounding the tie rod 4 ring segments 18 allow the compensation of the occurring during operation of the gas turbine, thermally induced expansion differences in the tangential direction.
  • 18 tangentially acting disc springs 20 are arranged in the circumference of the outer ring formed from the individual ring segments 18 between the ring segments.
  • Each of the Tangentialfederemia 24 is formed in this embodiment each of two series-connected disc springs 20, wherein each of the tangentially acting spring elements 24 is equally dimensioned.
  • the system integrated in the rotor 2 is constructed symmetrically with respect to the axis of rotation.
  • the provided with the radial spring elements 22 guide elements 14 and the Tangentialfederlude 24 each offset by 120 ° to each other about the axis of rotation around, wherein the radial spring elements 22 with respect to the Tangentialfederemia 24 are mutually offset by 60 °.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07005083A 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique Withdrawn EP1970528A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07005083A EP1970528A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07005083A EP1970528A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique

Publications (1)

Publication Number Publication Date
EP1970528A1 true EP1970528A1 (fr) 2008-09-17

Family

ID=38599395

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07005083A Withdrawn EP1970528A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique

Country Status (1)

Country Link
EP (1) EP1970528A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014195091A1 (fr) * 2013-06-04 2014-12-11 Siemens Aktiengesellschaft Agencement d'arbre de liaison de turbine à gaz comprenant une coque disposée entre l'arbre de liaison et le rotor
EP2985413A1 (fr) * 2014-08-13 2016-02-17 Siemens Aktiengesellschaft Réduction active d'oscillations mécaniques d'un arbre de rotor de turbine
EP3176366A1 (fr) * 2015-12-01 2017-06-07 Doosan Heavy Industries & Construction Co., Ltd. Disque et turbine comprenant celui-ci
US20180135416A1 (en) * 2016-11-17 2018-05-17 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine
IT202100010781A1 (it) * 2021-04-28 2022-10-28 Nuovo Pignone Tecnologie Srl Rotore di turbomacchina con giranti impilate e turbomacchina

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH259566A (de) * 1947-08-09 1949-01-31 Sulzer Ag Läufer für Kreiselmaschinen, insbesondere Gasturbinen.
US2635483A (en) * 1949-12-30 1953-04-21 Curtiss Wright Corp Vibration damper
GB770120A (en) * 1955-05-09 1957-03-13 Gen Motors Corp Improvements in the manufacture of axial compressor rotors
AU460687B2 (en) * 1971-12-13 1975-04-17 Kraftwerk Union Aktiengesellschaft Improvements in or relating toa rotor ofa disc-construction
US4160390A (en) * 1977-06-16 1979-07-10 Spaetgens Theodore W Tuned torsional vibration damper

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH259566A (de) * 1947-08-09 1949-01-31 Sulzer Ag Läufer für Kreiselmaschinen, insbesondere Gasturbinen.
US2635483A (en) * 1949-12-30 1953-04-21 Curtiss Wright Corp Vibration damper
GB770120A (en) * 1955-05-09 1957-03-13 Gen Motors Corp Improvements in the manufacture of axial compressor rotors
AU460687B2 (en) * 1971-12-13 1975-04-17 Kraftwerk Union Aktiengesellschaft Improvements in or relating toa rotor ofa disc-construction
US4160390A (en) * 1977-06-16 1979-07-10 Spaetgens Theodore W Tuned torsional vibration damper

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105308265B (zh) * 2013-06-04 2018-04-27 西门子股份公司 包括设置在系轴和转子之间的壳的燃气涡轮机系轴装置
WO2014195091A1 (fr) * 2013-06-04 2014-12-11 Siemens Aktiengesellschaft Agencement d'arbre de liaison de turbine à gaz comprenant une coque disposée entre l'arbre de liaison et le rotor
EP2985413A1 (fr) * 2014-08-13 2016-02-17 Siemens Aktiengesellschaft Réduction active d'oscillations mécaniques d'un arbre de rotor de turbine
WO2016023850A1 (fr) * 2014-08-13 2016-02-18 Siemens Aktiengesellschaft Réduction active des vibrations mécaniques d'un arbre de rotor d'une turbine
US10633973B2 (en) 2015-12-01 2020-04-28 DOOSAN Heavy Industries Construction Co., LTD Disk assembly and turbine including the same
EP3176366A1 (fr) * 2015-12-01 2017-06-07 Doosan Heavy Industries & Construction Co., Ltd. Disque et turbine comprenant celui-ci
US20180135416A1 (en) * 2016-11-17 2018-05-17 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine
EP3323980A1 (fr) * 2016-11-17 2018-05-23 Doosan Heavy Industries & Construction Co., Ltd. Turbine à gaz
JP2018080700A (ja) * 2016-11-17 2018-05-24 ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド ガスタービン
US10731468B2 (en) 2016-11-17 2020-08-04 Doosan Heavy Industries Construction Co., Ltd. Gas turbine
IT202100010781A1 (it) * 2021-04-28 2022-10-28 Nuovo Pignone Tecnologie Srl Rotore di turbomacchina con giranti impilate e turbomacchina
WO2022228727A1 (fr) 2021-04-28 2022-11-03 Nuovo Pignone Tecnologie - S.R.L. Rotor de turbomachine avec rouets empilés, et turbomachine
AU2022266952B2 (en) * 2021-04-28 2023-12-21 Nuovo Pignone Tecnologie - S.R.L. Turbomachine rotor with stacked impellers and turbomachine
JP2024514772A (ja) * 2021-04-28 2024-04-03 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータ 積み重ねられたインペラを備えたターボ機械ロータ及びターボ機械
JP7515029B2 (ja) 2021-04-28 2024-07-11 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータ 積み重ねられたインペラを備えたターボ機械ロータ及びターボ機械
US12215708B2 (en) 2021-04-28 2025-02-04 Nuovo Pignone Tecnologie—S.R.L. Turbomachine rotor with stacked impellers and turbomachine

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