SU658299A1 - Axial-flow turbomachine multiexhaust stage - Google Patents
Axial-flow turbomachine multiexhaust stageInfo
- Publication number
- SU658299A1 SU658299A1 SU772545256A SU2545256A SU658299A1 SU 658299 A1 SU658299 A1 SU 658299A1 SU 772545256 A SU772545256 A SU 772545256A SU 2545256 A SU2545256 A SU 2545256A SU 658299 A1 SU658299 A1 SU 658299A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- stage
- axial
- multiexhaust
- flow turbomachine
- blades
- Prior art date
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
II
Изобретение относитс к турбиностроению и может быть использовано в мощных паровых и газовых турбинах с двухъ русными осевыми ступен ми.The invention relates to turbine engineering and can be used in high-power steam and gas turbines with two-stage axial stages.
Известна двухъ русна ступень осевой турбомашины с разделенными кольцевыми межъ русными перегородками рабочей и направл ющей решетками 1. Эта ступень имеет, однако, невысокую экономичность.There is a known two-stage stage axial turbomachine with divided annular intermechanical partitions of the working and guide grids 1. This stage, however, has a low efficiency.
Наиболее близкой к изобретению по технической сущности вл етс двухъ русна The closest to the invention to the technical essence is two Russian
ступень осевой турбомашины с разделенными кольцевыми межъ русными перегородками рабочей и направл ющей решетками, в последней их которых лопатки верхнего руса в месте расположени межъ русной перегородки смещены по потоку относительно лопаток нижнего руса. Между выступаю1л .ими в осевой зазор участками кольцевых межъ русных перегородок установлено осевое лабиринтное уплотнение. 2J.a stage of an axial turbomachine with divided annular interme- diate partitions of the working and guide grids, in the last of which the upper-blade blades at the location of the inter-bulkhead are shifted downstream of the lower-blade blades. Between the protrusions, the axial labyrinth consolidation was established in the axial gap by the sections of the annular inter-Russian partitions. 2J.
В мощных осевых турбинах диаметр и радиальные зазоры уплотнени достаточно велики. Это приводит к снижению экономичности ступени из-за значительных протечек рабочего тела через зазор между межъ русными перегородками, что вл етс недостатком ступени.In powerful axial turbines, the diameter and radial clearances of the seal are large enough. This leads to a decrease in the economics of the stage due to significant leakage of the working fluid through the gap between the inter-septum walls, which is a disadvantage of the stage.
Цель изобретени - повышение экономичности двухъ русной ступени путем уменьшени протечек рабочего тела из нижнего руса в верхний.The purpose of the invention is to increase the efficiency of the two-stage stage by reducing the leakage of the working fluid from the lower to the upper russe.
Поставленна цель достигаетс тем, что выходна и входна кромки межъ русных перегородок соответственно направл ющей и рабочей решеток расположены между выходными кромками направл ющих ,топатокThe goal is achieved by the fact that the exit and entrance edges of the inter-Russian partitions, respectively, of the guide and working gratings are located between the exit edges of the guide, tok
верхнего и нижнего русов.top and bottom rusov.
На чертеже представлена двухъ русна предпоследн ступень мощной конденсационной паровой турбины, меридиональное сечение .The drawing shows a two-stage penultimate stage of a powerful condensing steam turbine, a meridional section.
Ступень содержит направл ющую и ра бочую решетки, состо щие из лопаток 1, 2 верхнего руса, и лопаток 3, 4 нижнего руса , разделенных кольцевыми межъ русными перегородками 5, 6 соответственно. В месте расположени межъ русных перегородок лоO патки 1, 2 верхнего руса смещены вперед по потоку относительно лопаток 3, 4 нижнего руса. Выходные кромки 7 лопаток 1 расположены впереди выходных кромок 8 лопаток 3.The stage contains guide and working grids consisting of blades 1, 2 of the upper rus, and blades 3, 4 of the lower rus, separated by annular interflux partitions 5, 6, respectively. At the location of the international margins, the wooden paths 1, 2 of the upper tusk are shifted downstream with respect to the blades 3, 4 of the lower tusk. The output edges 7 of the blades 1 are located in front of the output edges 8 of the blades 3.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU772545256A SU658299A1 (en) | 1977-11-18 | 1977-11-18 | Axial-flow turbomachine multiexhaust stage |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU772545256A SU658299A1 (en) | 1977-11-18 | 1977-11-18 | Axial-flow turbomachine multiexhaust stage |
Publications (1)
Publication Number | Publication Date |
---|---|
SU658299A1 true SU658299A1 (en) | 1979-04-25 |
Family
ID=20733775
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU772545256A SU658299A1 (en) | 1977-11-18 | 1977-11-18 | Axial-flow turbomachine multiexhaust stage |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU658299A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4213279A1 (en) * | 1992-04-16 | 1993-10-21 | Edgar Waitz | Multistage axial flow compressor - has sequence of impeller crowns with one crown having opposite flow direction to adjacent crown |
WO1994002727A1 (en) * | 1992-07-20 | 1994-02-03 | Smeshannoe Tovarischestvo 'germes' | Method for conversion of thermal energy into mechanical energy in gas-turbine engine and gas-turbine engine |
-
1977
- 1977-11-18 SU SU772545256A patent/SU658299A1/en active
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4213279A1 (en) * | 1992-04-16 | 1993-10-21 | Edgar Waitz | Multistage axial flow compressor - has sequence of impeller crowns with one crown having opposite flow direction to adjacent crown |
WO1994002727A1 (en) * | 1992-07-20 | 1994-02-03 | Smeshannoe Tovarischestvo 'germes' | Method for conversion of thermal energy into mechanical energy in gas-turbine engine and gas-turbine engine |
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