RU2012119374A - GAS TURBINE ENGINE AND METHOD FOR REGULATING RADIAL GAP IN A TURBINE OF A GAS TURBINE ENGINE - Google Patents
GAS TURBINE ENGINE AND METHOD FOR REGULATING RADIAL GAP IN A TURBINE OF A GAS TURBINE ENGINE Download PDFInfo
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- RU2012119374A RU2012119374A RU2012119374/06A RU2012119374A RU2012119374A RU 2012119374 A RU2012119374 A RU 2012119374A RU 2012119374/06 A RU2012119374/06 A RU 2012119374/06A RU 2012119374 A RU2012119374 A RU 2012119374A RU 2012119374 A RU2012119374 A RU 2012119374A
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- turbine
- radial clearance
- gas turbine
- turbine engine
- cooling
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Abstract
1. Газотурбинный двигатель, содержащий компрессор, имеющий по меньшей мере одну ступень, камеру сгорания, содержащую жаровую трубу, установленную с зазором относительно корпуса камеры сгорания, турбину, содержащую, по меньшей мере одну охлаждаемую ступень с сопловым аппаратом с полостями над ним и под ним, и ротор турбины с охлаждаемым рабочим колесом и аппаратом закрутки перед ним, а также статор турбины, содержащий, по меньшей мере два корпуса турбины с полостями между ними и систему регулирования радиального зазора, содержащую кольцевую вставку над рабочим колесом турбины, отличающийся тем, что полость над сопловым аппаратом соединена трубопроводом отбора воздуха, содержащим регулятор расхода с выходом из компрессора, а одна из полостей между корпусами турбины соединена трубопроводом, содержащим второй регулятор расхода с промежуточной ступенью компрессора, система регулирования радиального зазора содержит бортовой компьютер и датчики измерения радиального зазора, регулятор расхода, приводы клапанов, и датчики измерения радиального зазора соединены электрическими связями.2. Способ регулирования радиального зазора в турбине газотурбинного двигателя, включающий охлаждение ротора и статора, отличающийся тем, что измеряют радиальный зазор и в зависимости от его величины производят изменение расхода охлаждающего воздуха для охлаждения статора турбины, при этом расход охлаждающего воздуха для охлаждения ротора турбины изменяют в зависимости от режима работы ГТД, например, температуры газов перед турбиной.3. Способ регулирования радиального зазора в турбине газотурбинного двигателя по п.1, отличающ�1. A gas turbine engine containing a compressor having at least one stage, a combustion chamber containing a heat pipe mounted with a gap relative to the housing of the combustion chamber, a turbine containing at least one cooled stage with a nozzle apparatus with cavities above and below it and a turbine rotor with a cooled impeller and a spinning apparatus in front of it, as well as a turbine stator containing at least two turbine bodies with cavities between them and a radial clearance control system comprising an annulus an insert above the turbine impeller, characterized in that the cavity above the nozzle apparatus is connected by an air intake pipe containing a flow regulator with an outlet from the compressor, and one of the cavities between the turbine bodies is connected by a pipeline containing a second flow regulator with an intermediate compressor stage, a radial clearance control system contains an on-board computer and radial clearance sensors, a flow controller, valve actuators, and radial clearance sensors are electrically connected and svyazyami.2. A method for controlling the radial clearance in a turbine of a gas turbine engine, comprising cooling the rotor and stator, characterized in that the radial clearance is measured and, depending on its size, a change in the flow rate of cooling air is used to cool the turbine stator, while the flow rate of cooling air for cooling the turbine rotor is changed depending from the operation mode of the gas turbine engine, for example, the temperature of the gases in front of the turbine. 3. The method for controlling the radial clearance in a turbine of a gas turbine engine according to claim 1, characterized in
Claims (3)
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RU2012119374/06A RU2506435C2 (en) | 2012-05-11 | 2012-05-11 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
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RU2012119374/06A RU2506435C2 (en) | 2012-05-11 | 2012-05-11 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
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RU2012119374A true RU2012119374A (en) | 2013-11-20 |
RU2506435C2 RU2506435C2 (en) | 2014-02-10 |
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RU2012119374/06A RU2506435C2 (en) | 2012-05-11 | 2012-05-11 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113518850A (en) * | 2018-11-30 | 2021-10-19 | 西门子能源全球两合公司 | Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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RU2598964C2 (en) * | 2014-12-12 | 2016-10-10 | Федеральное агентство научных организаций Федеральное Государственное Бюджетное Научное Учреждение Всероссийский научно-исследовательский институт электрификации сельского хозяйства (ФГБНУ ВИЭСХ) | Combustion chamber with adjustable opening to supply cooling air for micro gas turbine engine |
RU2704056C2 (en) * | 2017-06-07 | 2019-10-23 | федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королёва" | Turbine of double-flow gas turbine engine with active thermal control of radial clearance in turbine, method of active thermal control of radial clearance in turbine of double-flow gas turbine engine |
RU2738523C1 (en) * | 2020-03-24 | 2020-12-14 | Николай Борисович Болотин | Control method of radial clearances of turbine of double-flow gas turbine engine and device for implementation thereof |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
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SU1809127A1 (en) * | 1977-07-13 | 1993-04-15 | Motornyj Z | Gas-turbine engine turbine |
GB2104966B (en) * | 1981-06-26 | 1984-08-01 | United Technologies Corp | Closed loop control for tip clearance of a gas turbine engine |
FR2766232B1 (en) * | 1997-07-18 | 1999-08-20 | Snecma | CIRCULAR HOUSING COOLING OR HEATING DEVICE |
RU2159335C1 (en) * | 1999-04-28 | 2000-11-20 | Открытое акционерное общество "А.Люлька-Сатурн" | Method of cooling turbine wheel rotor of multimode turbojet engine |
FR2891300A1 (en) * | 2005-09-23 | 2007-03-30 | Snecma Sa | DEVICE FOR CONTROLLING PLAY IN A GAS TURBINE |
RU2316662C1 (en) * | 2006-04-03 | 2008-02-10 | Открытое акционерное общество "Авиадвигатель" | Gas-turbine engine |
RU2387846C1 (en) * | 2008-10-29 | 2010-04-27 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Method to cool by-pass gas turbine engine vanes and device to this end |
US8307662B2 (en) * | 2009-10-15 | 2012-11-13 | General Electric Company | Gas turbine engine temperature modulated cooling flow |
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2012
- 2012-05-11 RU RU2012119374/06A patent/RU2506435C2/en active
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113518850A (en) * | 2018-11-30 | 2021-10-19 | 西门子能源全球两合公司 | Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance |
CN113518850B (en) * | 2018-11-30 | 2023-08-29 | 西门子能源全球两合公司 | Mid-frame section of a gas turbine engine and corresponding method of adjusting radial rotor clearance |
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RU2506435C2 (en) | 2014-02-10 |
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