SU1663202A1 - Stator of turbo-driven set - Google Patents
Stator of turbo-driven set Download PDFInfo
- Publication number
- SU1663202A1 SU1663202A1 SU884423242A SU4423242A SU1663202A1 SU 1663202 A1 SU1663202 A1 SU 1663202A1 SU 884423242 A SU884423242 A SU 884423242A SU 4423242 A SU4423242 A SU 4423242A SU 1663202 A1 SU1663202 A1 SU 1663202A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- channels
- diaphragm
- turbomachine
- rings
- flow part
- Prior art date
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Изобретение относитс к турбостроению. Целью изобретени вл етс повышение надежности путем обеспечени автоматического регулировани . Статор турбомашины содержит корпус 1, внутри которого установлены сопловые лопатки 2 со сквозными каналами 3, конические кольца 4 с каналами, установленные с осевым зазором относительно друг друга, и устройство дл перемещени колец 4, выполненное в виде диафрагмы 7 с каналами 8, соответствующие входы и выходы которых размещены в различных диаметральных плоскост х. Диафрагма 7 дл перемещени колец 4 сообщена с проточной частью турбомашины посредством сквозных каналов 3 в сопловых лопатках 2. Диафрагма 7 выполнена из тонкостенных конструкций с элементами жесткости и имеет теплоинерционность меньшую, чем теплоинерционность конических колец 4. Входы каналов 8 сообщены со сквозными каналами 3 сопловых лопаток 2. На выходе из каналов 8 диафрагмы 7 установлен коллектор с дренажным клапаном. В канале 8 диафрагмы 7 могут быть установлены гофрированные вставки, которые образуют два канала, при этом вход одного канала подключен к проточной части турбомашины, а выход - к коллектору, вход другого канала подключен к проточной части турбомашины, а выход - к полости за компрессором (на чертеже не показан). Полости 14 между диафрагмами 7 подключены к полости за компрессором. 1 з.п.ф-лы, 2 ил.FIELD: turbine engineering. The aim of the invention is to increase reliability by providing automatic control. The stator of the turbomachine comprises a housing 1, inside which are mounted nozzle vanes 2 with through channels 3, conical rings 4 with channels installed with an axial clearance relative to each other, and a device for moving rings 4, made in the form of a diaphragm 7 with channels 8, the corresponding inputs and the outlets of which are located in different diametrical planes. The diaphragm 7 for moving the rings 4 communicates with the flow part of the turbomachine through the through channels 3 in the nozzle vanes 2. The diaphragm 7 is made of thin-walled structures with rigidity elements and has a heat inertia less than the inertia of the conical rings 4. The inlets of the channels 8 are connected with the through channels 3 nozzle blades 2. At the outlet of the channels 8 of the diaphragm 7 a collector with a drain valve is installed. The channel 8 of the diaphragm 7 can be fitted with corrugated inserts that form two channels, with the input of one channel connected to the flow part of the turbomachine, and the output to the collector, the input of the other channel connected to the flow part of the turbomachine, and not shown in the drawing). Cavity 14 between the diaphragms 7 are connected to the cavity behind the compressor. 1 hp ff, 2 ill.
Description
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Claims (2)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU884423242A SU1663202A1 (en) | 1988-05-12 | 1988-05-12 | Stator of turbo-driven set |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU884423242A SU1663202A1 (en) | 1988-05-12 | 1988-05-12 | Stator of turbo-driven set |
Publications (1)
Publication Number | Publication Date |
---|---|
SU1663202A1 true SU1663202A1 (en) | 1991-07-15 |
Family
ID=21374066
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU884423242A SU1663202A1 (en) | 1988-05-12 | 1988-05-12 | Stator of turbo-driven set |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU1663202A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2476710C2 (en) * | 2007-11-13 | 2013-02-27 | Снекма | Rotor ring seal in turbine stage |
-
1988
- 1988-05-12 SU SU884423242A patent/SU1663202A1/en active
Non-Patent Citations (1)
Title |
---|
Авторское свидетельство СССР № 1020649, кл. F 04 D 29/08, 1979. * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2476710C2 (en) * | 2007-11-13 | 2013-02-27 | Снекма | Rotor ring seal in turbine stage |
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