RU2013119145A - TURBINE OF A GAS-TURBINE ENGINE AND METHOD FOR ADJUSTING A RADIAL GAP IN A TURBINE - Google Patents
TURBINE OF A GAS-TURBINE ENGINE AND METHOD FOR ADJUSTING A RADIAL GAP IN A TURBINE Download PDFInfo
- Publication number
- RU2013119145A RU2013119145A RU2013119145/06A RU2013119145A RU2013119145A RU 2013119145 A RU2013119145 A RU 2013119145A RU 2013119145/06 A RU2013119145/06 A RU 2013119145/06A RU 2013119145 A RU2013119145 A RU 2013119145A RU 2013119145 A RU2013119145 A RU 2013119145A
- Authority
- RU
- Russia
- Prior art keywords
- turbine
- radial clearance
- gas turbine
- annular insert
- turbine engine
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract 3
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 2
- 238000005259 measurement Methods 0.000 claims abstract 4
- 238000001816 cooling Methods 0.000 claims abstract 2
- 238000005070 sampling Methods 0.000 claims abstract 2
- 230000001105 regulatory effect Effects 0.000 claims 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1. Турбина газотурбинного двигателя, содержащая, по меньшей мере, одну охлаждаемую ступень с сопловым аппаратом с полостями над ним и под ним, и ротор турбины с охлаждаемым рабочим колесом, 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, отличающаяся тем, что полость над сопловым аппаратом соединена трубопроводом отбора воздуха, содержащим регулятор расхода с выходом из компрессора, система регулирования радиального зазора содержит бортовой компьютер, датчики измерения радиального зазора, установленные над вставкой при этом датчики измерения радиального зазора соединены электрическими связями с бортовым компьютером, а кольцевая вставка выполнена из материала с высоким удельным сопротивлением и соединена силовыми кабелями через коммутатор с источником энергии..2. Турбина газотурбинного двигателя по п.1, отличающаяся тем, что кольцевая вставка выполнена пустотелой.3. Турбина газотурбинного двигателя по п.1 или 2, отличающаяся тем, что кольцевая вставка выполнена из сегментов.4. Турбина газотурбинного двигателя по п.1 или 2, отличающаяся тем, что кольцевая вставка электрически изолирована относительно статора турбины.5. Турбина газотурбинного двигателя по п.3, отличающаяся тем, что кольцевая вставка электрически изолирована относительно статора турбины6. Способ регулирования радиального зазора в турбине газотурбинного двигателя, включающий охлаждение ротора статора, отличающийся тем, что измеряют радиальный зазор и в зависимости от его величины производят в�1. A turbine of a gas turbine engine, comprising 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 turbine stator containing at least two turbine bodies with cavities between them and a radial clearance control system comprising an annular insert above the turbine impeller, characterized in that the cavity above the nozzle apparatus is connected by an air sampling pipe containing a flow regulator with an outlet from the compressor, the system p The radial clearance control contains an on-board computer, radial clearance measurement sensors installed above the insert, while the radial clearance measurement sensors are electrically connected to the on-board computer, and the ring insert is made of high resistivity material and is connected by power cables through a switch with an energy source. 2 . The turbine of a gas turbine engine according to claim 1, characterized in that the annular insert is made hollow. The gas turbine engine turbine according to claim 1 or 2, characterized in that the annular insert is made of segments. The gas turbine engine turbine according to claim 1 or 2, characterized in that the annular insert is electrically isolated relative to the turbine stator. The gas turbine engine turbine according to claim 3, characterized in that the annular insert is electrically isolated relative to the turbine stator 6. A method for controlling the radial clearance in a turbine of a gas turbine engine, comprising cooling the stator rotor, characterized in that the radial clearance is measured and, depending on its size, produce
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2013119145/06A RU2535453C1 (en) | 2013-04-24 | 2013-04-24 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2013119145/06A RU2535453C1 (en) | 2013-04-24 | 2013-04-24 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2013119145A true RU2013119145A (en) | 2014-10-27 |
| RU2535453C1 RU2535453C1 (en) | 2014-12-10 |
Family
ID=53285957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2013119145/06A RU2535453C1 (en) | 2013-04-24 | 2013-04-24 | Gas turbine engine and method for radial clearance adjustment in gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2535453C1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2732653C1 (en) * | 2020-03-24 | 2020-09-21 | Николай Борисович Болотин | Method of cooling and regulating radial clearances of turbine of double-flow gas turbine engine and device for implementation thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1137783B (en) * | 1981-08-03 | 1986-09-10 | Nuovo Pignone Spa | HEAT EXCHANGER INTEGRATED WITH THE STATIC CASE OF A GAS TURBINE |
| GB0308147D0 (en) * | 2003-04-09 | 2003-05-14 | Rolls Royce Plc | A seal |
| FR2890685B1 (en) * | 2005-09-14 | 2007-12-14 | Snecma | TURBINE HIGH ROTOR ROTOR AUTONOMOUS ROTOR CONTROL IN A TURBOMACHINE |
| FR2943717B1 (en) * | 2009-03-27 | 2016-02-19 | Snecma | COMPRESSOR STATOR OR TURBINE ENGINE TURBINE FOR CONTROLLING THE AUTHORED GAME OF A ROTOR IN LOOK |
| FR2949808B1 (en) * | 2009-09-08 | 2011-09-09 | Snecma | PILOTAGE OF THE AUBES IN A TURBOMACHINE |
-
2013
- 2013-04-24 RU RU2013119145/06A patent/RU2535453C1/en active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2535453C1 (en) | 2014-12-10 |
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