RU2012138768A - TWO-CIRCUIT GAS TURBINE ENGINE AND METHOD FOR REGULATING RADIAL CLEARANCE IN A TURBINE OF A TWO-CIRCUIT GAS TURBINE ENGINE - Google Patents
TWO-CIRCUIT GAS TURBINE ENGINE AND METHOD FOR REGULATING RADIAL CLEARANCE IN A TURBINE OF A TWO-CIRCUIT GAS TURBINE ENGINE Download PDFInfo
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- RU2012138768A RU2012138768A RU2012138768/06A RU2012138768A RU2012138768A RU 2012138768 A RU2012138768 A RU 2012138768A RU 2012138768/06 A RU2012138768/06 A RU 2012138768/06A RU 2012138768 A RU2012138768 A RU 2012138768A RU 2012138768 A RU2012138768 A RU 2012138768A
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- turbine
- air
- stator
- cooling
- radial clearance
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Abstract
1. Двухконтурный газотурбинный двигатель, содержащий компрессор, камеру сгорания, турбину, содержащую, по меньшей мере, одну охлаждаемую ступень с сопловым аппаратом с полостями над ним и под ним, и по меньшей мере один ротор турбины с охлаждаемым рабочим колесом и аппаратом закрутки перед ним, а также статор турбины, содержащий, по меньшей мере один корпус турбины с полостями между ними и кольцевую вставку над рабочим колесом турбины и систему регулирования радиального зазора, отличающийся тем, что статор турбины выполнен охлаждаемым воздухом второго контура, при этом система подачи охлаждающего статор воздуха выполнена в виде воздухозаборника, установленного во втором контуре и регулятора расхода с приводом, и также содержит бортовой компьютер и датчики измерения радиального зазора, привод регулятора расхода, и датчики измерения радиального зазора соединены электрическими связями с бортовым компьютером.2. Двухконтурный газотурбинный двигатель по п.1, отличающийся тем, что кольцевая вставка выполнена пустотелой.3. Двухконтурный газотурбинный двигатель по п.2, отличающийся тем, что внутренняя полость вставки заполнена теплоаккумулирующим веществом.4. Способ регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя, включающий охлаждение ротора воздухом высокого давления отбираемым из-за компрессора и статора воздухом второго контура, отличающийся тем, что для охлаждения статора турбины используют часть расхода воздуха второго контура, который отбирают используя воздухозаборник и увеличивают скорость охлаждающего воздуха в тракте охлаждения статора турбины, измеряют ради1. A double-circuit gas turbine engine containing a compressor, a combustion chamber, a turbine containing at least one cooled stage with a nozzle apparatus with cavities above and below it, and at least one turbine rotor with a cooled impeller and a spin apparatus in front of it as well as a turbine stator, comprising at least one turbine casing with cavities between them and an annular insert above the turbine impeller and a radial clearance control system, characterized in that the turbine stator is cooled by air the ear of the second circuit, while the cooling stator air supply system is made in the form of an air intake installed in the second circuit and a flow regulator with a drive, and also contains an on-board computer and radial clearance measurement sensors, a flow regulator drive, and radial clearance measurement sensors are connected by electrical connections with on-board computer. 2. A dual-circuit gas turbine engine according to claim 1, characterized in that the annular insert is made hollow. The dual-circuit gas turbine engine according to claim 2, characterized in that the inner cavity of the insert is filled with a heat-accumulating substance. A method for regulating the radial clearance in a turbine of a double-circuit gas turbine engine, comprising cooling the rotor with high-pressure air taken from the compressor and the stator of the secondary air, characterized in that a part of the secondary air flow is used to cool the turbine stator, which is taken using the air intake and the cooling speed is increased air in the cooling path of the turbine stator, measured for
Claims (4)
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RU2012138768/06A RU2511860C1 (en) | 2012-09-10 | 2012-09-10 | Double-flow gas turbine engine, and adjustment method of radial gap in turbine of double-flow gas turbine engine |
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RU2012138768/06A RU2511860C1 (en) | 2012-09-10 | 2012-09-10 | Double-flow gas turbine engine, and adjustment method of radial gap in turbine of double-flow gas turbine engine |
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RU2012138768A true RU2012138768A (en) | 2014-03-20 |
RU2511860C1 RU2511860C1 (en) | 2014-04-10 |
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RU2012138768/06A RU2511860C1 (en) | 2012-09-10 | 2012-09-10 | Double-flow gas turbine engine, and adjustment method of radial gap in turbine of double-flow gas turbine engine |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112417658A (en) * | 2020-11-11 | 2021-02-26 | 南京航空航天大学 | Design point parameter cycle modeling method for double-bypass variable-cycle engine |
Family Cites Families (4)
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 |
RU2151886C1 (en) * | 1998-08-04 | 2000-06-27 | Открытое акционерное общество "Авиадвигатель" | Stator of multistage gas turbine |
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 |
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2012
- 2012-09-10 RU RU2012138768/06A patent/RU2511860C1/en active
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112417658A (en) * | 2020-11-11 | 2021-02-26 | 南京航空航天大学 | Design point parameter cycle modeling method for double-bypass variable-cycle engine |
CN112417658B (en) * | 2020-11-11 | 2024-03-29 | 南京航空航天大学 | Design point parameter cycle modeling method for double-external culvert variable cycle engine |
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RU2511860C1 (en) | 2014-04-10 |
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