RU2013105342A - COMPRESSOR AND RELATED GAS TURBINE - Google Patents

COMPRESSOR AND RELATED GAS TURBINE Download PDF

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Publication number
RU2013105342A
RU2013105342A RU2013105342/06A RU2013105342A RU2013105342A RU 2013105342 A RU2013105342 A RU 2013105342A RU 2013105342/06 A RU2013105342/06 A RU 2013105342/06A RU 2013105342 A RU2013105342 A RU 2013105342A RU 2013105342 A RU2013105342 A RU 2013105342A
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RU
Russia
Prior art keywords
compressor
ring
inner ring
spring element
gap
Prior art date
Application number
RU2013105342/06A
Other languages
Russian (ru)
Other versions
RU2575956C2 (en
Inventor
Томас БРАНДЕНБУРГ
Даниэль ЭКЕ
Маркус ХОФМАНН
Торстен МАТТИАС
Бернвард МЕРТЕНС
Франк МИЛЬДНЕР
Маркус ПАУС
Ахим ШИРРМАХЕР
Вадим ШЕВЧЕНКО
Уве ЗИБЕР
Хубертус Михаэль ВИГГЕР
Original Assignee
Сименс Акциенгезелльшафт
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Publication date
Application filed by Сименс Акциенгезелльшафт filed Critical Сименс Акциенгезелльшафт
Publication of RU2013105342A publication Critical patent/RU2013105342A/en
Application granted granted Critical
Publication of RU2575956C2 publication Critical patent/RU2575956C2/en

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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rotary Pumps (AREA)

Abstract

1. Компрессор (10), содержащий ограничивающий радиально снаружи кольцеобразный проточный канал (36) корпус, в котором удерживаются с возможностью поворота проходящие через проточный канал (36) направляющие лопатки (14) венца направляющих лопаток, при этом каждая направляющая лопатка (14) имеет на стороне корпуса проходящую через корпус первую цапфу (26) и на стороне ротора выступающую во внутреннее кольцо (32) вторую цапфу (26), отличающийся тем, что внутреннее кольцо (32) выполнено в виде имеющего зазор кольца с двумя лежащими противоположно друг другу концами (44) и снабжено пружинным элементом (52) для разжимания кольца с зазором.2. Компрессор (10) по п.1, в котором оба конца (44) кольца с зазором имеют лежащие противоположно друг другу первые гнезда (50), в которых установлен пружинный элемент (52).3. Компрессор (10) по любому из пп.1 или 2, в котором пружинный элемент (52) заключен в кожух.4. Компрессор (10) по любому из пп.1 или 2, в котором концы фиксированы в осевом направлении.5. Компрессор (10) по любому из пп.1 или 2, в котором внутреннее кольцо (32) содержит по меньшей мере два сегмента (40).6. Компрессор (10) по любому из пп.1 или 2, в котором на вторых цапфах (26) расположена соответствующая втулка (28) с буртиком.7. Компрессор (10) по любому из пп.1 или 2, в котором вторая цапфа (26) имеет бесконечную окружную канавку (24) с установленным в ней уплотнительным кольцом.8. Компрессор (10) по любому из пп.1 или 2, в котором внутреннее кольцо (32), соответственно сегменты, выполнены с возможностью разделения в осевом направлении.9. Газовая турбина, содержащая компрессор (10) по любому из пп.1-8.1. Compressor (10), comprising a radially outwardly limiting annular flow channel (36), in which guide vanes (14) passing through the flow channel (36) are held rotatably, each guide vane (14) has on the side of the housing, the first journal (26) passing through the housing and on the side of the rotor protruding into the inner ring (32) the second journal (26), characterized in that the inner ring (32) is made in the form of a ring with a gap with two ends lying opposite to each other (44) and is equipped with a spring element (52) for opening the ring with a gap. 2. Compressor (10) according to claim 1, in which both ends (44) of the ring with a gap have oppositely located first seats (50), in which a spring element (52) is installed. Compressor (10) according to any one of claims 1 or 2, in which the spring element (52) is enclosed in a casing. 4. Compressor (10) according to any one of claims 1 or 2, in which the ends are fixed in the axial direction. Compressor (10) according to any one of claims 1 or 2, in which the inner ring (32) contains at least two segments (40). 6. Compressor (10) according to any one of claims 1 or 2, in which a corresponding collar sleeve (28) is located on the second trunnions (26). Compressor (10) according to any one of claims 1 or 2, in which the second trunnion (26) has an endless circumferential groove (24) with an O-ring installed therein. Compressor (10) according to any one of claims 1 or 2, in which the inner ring (32), respectively, segments are made with the possibility of separation in the axial direction. Gas turbine containing a compressor (10) according to any one of claims 1-8.

Claims (9)

1. Компрессор (10), содержащий ограничивающий радиально снаружи кольцеобразный проточный канал (36) корпус, в котором удерживаются с возможностью поворота проходящие через проточный канал (36) направляющие лопатки (14) венца направляющих лопаток, при этом каждая направляющая лопатка (14) имеет на стороне корпуса проходящую через корпус первую цапфу (26) и на стороне ротора выступающую во внутреннее кольцо (32) вторую цапфу (26), отличающийся тем, что внутреннее кольцо (32) выполнено в виде имеющего зазор кольца с двумя лежащими противоположно друг другу концами (44) и снабжено пружинным элементом (52) для разжимания кольца с зазором.1. A compressor (10) comprising a housing that defines a ring-shaped flow channel (36) that extends radially from the outside, and which holds the guide vanes (14) of the guide vane crown extending through the channel (36) and each guide vane (14) has on the casing side, the first pin (26) passing through the casing and on the rotor side, the second pin (26) protruding into the inner ring (32), characterized in that the inner ring (32) is made in the form of a ring having a gap with two opposite to each other ends (44) and is provided with a spring element (52) for unclamping ring with clearance. 2. Компрессор (10) по п.1, в котором оба конца (44) кольца с зазором имеют лежащие противоположно друг другу первые гнезда (50), в которых установлен пружинный элемент (52).2. The compressor (10) according to claim 1, in which both ends (44) of the ring with a gap have opposing to each other first sockets (50) in which a spring element (52) is installed. 3. Компрессор (10) по любому из пп.1 или 2, в котором пружинный элемент (52) заключен в кожух.3. The compressor (10) according to any one of claims 1 or 2, in which the spring element (52) is enclosed in a casing. 4. Компрессор (10) по любому из пп.1 или 2, в котором концы фиксированы в осевом направлении.4. The compressor (10) according to any one of claims 1 or 2, in which the ends are fixed in the axial direction. 5. Компрессор (10) по любому из пп.1 или 2, в котором внутреннее кольцо (32) содержит по меньшей мере два сегмента (40).5. The compressor (10) according to any one of claims 1 or 2, in which the inner ring (32) contains at least two segments (40). 6. Компрессор (10) по любому из пп.1 или 2, в котором на вторых цапфах (26) расположена соответствующая втулка (28) с буртиком.6. The compressor (10) according to any one of claims 1 or 2, in which a corresponding sleeve (28) with a shoulder is located on the second trunnion (26). 7. Компрессор (10) по любому из пп.1 или 2, в котором вторая цапфа (26) имеет бесконечную окружную канавку (24) с установленным в ней уплотнительным кольцом.7. Compressor (10) according to any one of claims 1 or 2, in which the second pin (26) has an infinite circumferential groove (24) with a sealing ring installed in it. 8. Компрессор (10) по любому из пп.1 или 2, в котором внутреннее кольцо (32), соответственно сегменты, выполнены с возможностью разделения в осевом направлении.8. The compressor (10) according to any one of claims 1 or 2, in which the inner ring (32), respectively, the segments are made with the possibility of separation in the axial direction. 9. Газовая турбина, содержащая компрессор (10) по любому из пп.1-8. 9. A gas turbine containing a compressor (10) according to any one of claims 1 to 8.
RU2013105342/06A 2010-07-08 2011-07-07 Compressor and appropriate gas turbine RU2575956C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10007062.2 2010-07-08
EP10007062A EP2405104A1 (en) 2010-07-08 2010-07-08 Compressor and corresponding gas turbine engine
PCT/EP2011/061486 WO2012004336A2 (en) 2010-07-08 2011-07-07 Compressor

Publications (2)

Publication Number Publication Date
RU2013105342A true RU2013105342A (en) 2014-08-20
RU2575956C2 RU2575956C2 (en) 2016-02-27

Family

ID=43221935

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2013105342/06A RU2575956C2 (en) 2010-07-08 2011-07-07 Compressor and appropriate gas turbine

Country Status (6)

Country Link
US (1) US20130216359A1 (en)
EP (2) EP2405104A1 (en)
JP (1) JP5638696B2 (en)
CN (1) CN102985640B (en)
RU (1) RU2575956C2 (en)
WO (1) WO2012004336A2 (en)

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US9341194B2 (en) 2012-11-01 2016-05-17 Solar Turbines Incorporated Gas turbine engine compressor with a biased inner ring
DE102016207212A1 (en) * 2016-04-28 2017-11-02 MTU Aero Engines AG Guide vane ring for a turbomachine
JP7349274B2 (en) * 2019-06-27 2023-09-22 三菱重工業株式会社 Stator blade support ring and turbine
CN112065777B (en) * 2020-11-10 2021-01-19 中国航发上海商用航空发动机制造有限责任公司 Adjusting precision maintaining structure of inlet guide vane of gas compressor
JP7439315B1 (en) 2023-03-16 2024-02-27 株式会社神鋼環境ソリューション cylindrical structure

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Also Published As

Publication number Publication date
EP2591213A2 (en) 2013-05-15
CN102985640B (en) 2015-10-21
RU2575956C2 (en) 2016-02-27
JP5638696B2 (en) 2014-12-10
EP2591213B1 (en) 2014-04-02
WO2012004336A3 (en) 2012-06-07
EP2405104A1 (en) 2012-01-11
JP2013529755A (en) 2013-07-22
WO2012004336A2 (en) 2012-01-12
US20130216359A1 (en) 2013-08-22
CN102985640A (en) 2013-03-20

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Effective date: 20170708