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RU2003102441A - GAS TURBINE SEALING SYSTEM - Google Patents

GAS TURBINE SEALING SYSTEM

Info

Publication number
RU2003102441A
RU2003102441A RU2003102441/06A RU2003102441A RU2003102441A RU 2003102441 A RU2003102441 A RU 2003102441A RU 2003102441/06 A RU2003102441/06 A RU 2003102441/06A RU 2003102441 A RU2003102441 A RU 2003102441A RU 2003102441 A RU2003102441 A RU 2003102441A
Authority
RU
Russia
Prior art keywords
seals
shock absorber
internal cavity
gas turbine
compressor
Prior art date
Application number
RU2003102441/06A
Other languages
Russian (ru)
Other versions
RU2270352C2 (en
Inventor
Алессандро КОППОЛА
Original Assignee
Нуово Пиньоне Холдинг С.П.А.
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
Priority claimed from IT2000MI001461A external-priority patent/IT1318065B1/en
Application filed by Нуово Пиньоне Холдинг С.П.А. filed Critical Нуово Пиньоне Холдинг С.П.А.
Publication of RU2003102441A publication Critical patent/RU2003102441A/en
Application granted granted Critical
Publication of RU2270352C2 publication Critical patent/RU2270352C2/en

Links

Claims (4)

1. Система (10) уплотнения и создания повышенного давления для амортизатора (24) опоры газовой турбины (20), где указанная газовая турбина (20) снабжена компрессором (21), связанным с внутренней полостью (23), при этом указанный амортизатор (24) опоры, в свою очередь, снабжен уплотнениями (38, 39) по отношению к оси компрессора (21) и имеет по меньшей мере одну вентиляционную трубу (33) для подачи воздуха через ее выпускное отверстие во внутреннюю полость (23) с тем, чтобы создать суммарный поток воздуха, который начинается от промежуточной ступени компрессора (21) и протекает по направлению к внутренней полости (23), отличающаяся тем, что подача воздуха обеспечивается как через уплотнения (38, 39), так и через боковое отверстие (42) вентиляционной трубы (33), так что первая часть суммарного потока воздуха передается во внутреннюю полость (23) с помощью отверстия (42) трубы (33).1. The system (10) of sealing and creating increased pressure for the shock absorber (24) of the support of the gas turbine (20), where the specified gas turbine (20) is equipped with a compressor (21) connected to the internal cavity (23), while the specified shock absorber (24 ) the supports, in turn, are equipped with seals (38, 39) with respect to the axis of the compressor (21) and have at least one ventilation pipe (33) for supplying air through its outlet to the internal cavity (23) so that create a total air flow that starts from the intermediate stage of the compressor (2 1) and flows towards the inner cavity (23), characterized in that the air supply is provided both through the seals (38, 39) and through the side opening (42) of the ventilation pipe (33), so that the first part of the total air flow transferred to the internal cavity (23) using the hole (42) of the pipe (33). 2. Система (10) по п.1, отличающаяся тем, что уплотнения (38, 39) имеют внутреннюю и внешнюю, разнесенные на расстояние по направлению оси, части уплотнений по отношению к вкладышу (37), так что вторая часть суммарного потока воздуха передается во внутреннюю полость (23) через внешнее лабиринтное уплотнение амортизатора (24).2. System (10) according to claim 1, characterized in that the seals (38, 39) have internal and external, spaced apart in the direction of the axis, parts of the seals with respect to the liner (37), so that the second part of the total air flow is transmitted to the internal cavity (23) through the external labyrinth seal of the shock absorber (24). 3. Система (10) по п.1, отличающаяся тем, что амортизатор (24) опоры включает в себя пневматический дроссельный клапан, регулируемый непосредственно с пульта управления, и электромеханический привод с датчиком положения клапана.3. System (10) according to claim 1, characterized in that the shock absorber (24) of the support includes a pneumatic throttle valve, adjustable directly from the control panel, and an electromechanical actuator with a valve position sensor. 4. Система (10) по п.2, отличающаяся тем, что внешнее лабиринтное уплотнение включает в себя отверстие (40) для прохода воздуха и уплотняющую гребенку (41).4. System (10) according to claim 2, characterized in that the external labyrinth seal includes an opening (40) for air passage and a sealing comb (41).
RU2003102441/06A 2000-06-29 2001-06-20 Gas turbine sealing-up system RU2270352C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT2000MI001461A IT1318065B1 (en) 2000-06-29 2000-06-29 SEALING AND PRESSURIZATION SYSTEM FOR THE BEARING OF A GAS TURBINE
ITMI2000A001461 2000-06-29

Publications (2)

Publication Number Publication Date
RU2003102441A true RU2003102441A (en) 2004-08-10
RU2270352C2 RU2270352C2 (en) 2006-02-20

Family

ID=11445369

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003102441/06A RU2270352C2 (en) 2000-06-29 2001-06-20 Gas turbine sealing-up system

Country Status (13)

Country Link
US (1) US6932349B2 (en)
EP (1) EP1299620B1 (en)
AR (1) AR028773A1 (en)
AT (1) ATE385280T1 (en)
AU (1) AU2001283875A1 (en)
BR (1) BR0112099A (en)
DE (1) DE60132667T2 (en)
EG (1) EG22843A (en)
IT (1) IT1318065B1 (en)
MX (1) MXPA03000045A (en)
NO (1) NO20026217L (en)
RU (1) RU2270352C2 (en)
WO (1) WO2002001046A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7575197B2 (en) * 2004-05-17 2009-08-18 The Boeing Company Mobile transporter servicing unit for an operational ground support system
EP1712816A1 (en) * 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Sealing system for sealing a process gas chamber from a chamber to be sealed
ATE461366T1 (en) * 2005-09-21 2010-04-15 High Technology Invest Bv BEARING SEAL ARRANGEMENT WITH LABYRINTH SEAL AND SCREW SEAL COMBINATION
JP4898743B2 (en) * 2008-06-09 2012-03-21 三菱重工業株式会社 Sealing structure of rotating machine
DE102008052101A1 (en) 2008-10-20 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Compressor for a gas turbine
US8740225B2 (en) * 2009-06-03 2014-06-03 Exponential Technologies, Inc. Hydrodynamic bore seal
EP2383440A1 (en) * 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Turbine including seal air valve system
DE102010028732A1 (en) * 2010-05-07 2011-11-10 Man Diesel & Turbo Se Labyrinth seal for a turbomachine
JP5827827B2 (en) * 2010-06-29 2015-12-02 エーエスエムエル ネザーランズ ビー．ブイ． Actuator
EP2431574A1 (en) 2010-09-20 2012-03-21 Siemens Aktiengesellschaft Gas turbine and method for operating a gas turbine
US20130287551A1 (en) * 2012-04-27 2013-10-31 General Electric Company Separable seal assembly for a gas turbine engine
US9028205B2 (en) * 2012-06-13 2015-05-12 United Technologies Corporation Variable blade outer air seal
PL3055595T3 (en) * 2013-10-10 2020-06-01 Weir Slurry Group Inc. Shaft seal assembly with contaminant detection system and corresponding method
DE102014011042A1 (en) * 2014-07-26 2016-01-28 Man Diesel & Turbo Se flow machine
CN111771061B (en) 2017-12-13 2023-02-10 益班修科技股份有限公司 Rotary fluid flow device
US11168683B2 (en) 2019-03-14 2021-11-09 Exponential Technologies, Inc. Pressure balancing system for a fluid pump

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB852805A (en) * 1958-08-20 1960-11-02 & Chantiers De Bretange Ancien Improvements to sealing means for the shafts of steam turbines
US4193603A (en) * 1978-12-21 1980-03-18 Carrier Corporation Sealing system for a turbomachine
RU2039872C1 (en) * 1991-07-05 1995-07-20 Пермское научно-производственное объединение "Авиадвигатель" Labyrinth seal for radial gap of turbo-machine
RU2036312C1 (en) * 1991-07-16 1995-05-27 Акционерное общество открытого типа "Авиадвигатель" Sealing unit downstream of turbojet double-loop engine
RU2134808C1 (en) * 1997-01-22 1999-08-20 Открытое акционерное общество "Авиадвигатель" Gas-turbine engine
RU2151897C1 (en) * 1997-12-16 2000-06-27 Открытое акционерное общество "Авиадвигатель" Gas turbine engine sealing device

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