JPS5569703A - Stepped construction for turbine - Google Patents
Stepped construction for turbineInfo
- Publication number
- JPS5569703A JPS5569703A JP14234778A JP14234778A JPS5569703A JP S5569703 A JPS5569703 A JP S5569703A JP 14234778 A JP14234778 A JP 14234778A JP 14234778 A JP14234778 A JP 14234778A JP S5569703 A JPS5569703 A JP S5569703A
- Authority
- JP
- Japan
- Prior art keywords
- ring
- edge portion
- groove portion
- stator blades
- guide grooves
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
PURPOSE: To enhance uniformity of flow at the inlet of rotor blades and to thereby reduce occurrence of vibrational stress and pressure loss due to non-steady flow of work fluid, by forming a plurality of guide grooves capable of receiving respective stator blades therein in the wall surface of diaphragm in the manner that they extend from the inlet end to the outlet end of work fluid.
CONSTITUTION: Stator blades 12 are fixed to outer ring 11a and inner ring 11b of diaphragm 11 and rotor blades 13 fixed to rotor disk 14 are disposed on the downstream side of stator blades 12. Here, guide grooves 17 are formed in the wall surface of outer ring 11a and inner ring 11b. These guide grooves 17 are shaped to have a straight groove portion 17a having a uniform width in the region from the top end of ring 11a (or 11b) to the leading edge portion of stator blades and to have a curved groove portion 17b in the region from said leading edge portion to the rear end portion of the ring. This straight groove portion 17a is formed to have a uniform depth whereas the curved groove portion 17b is formed such that its depth is reduced gradually from the trailing edge portion to the rear end of ring. By thus reducing the sectional area of the fluid passage gradually from the trailing edge portion 12b to the leading edge portion 13a of rotor blades, it is enabled to form a contract vein of fluid.
COPYRIGHT: (C)1980,JPO&Japio
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14234778A JPS5851121B2 (en) | 1978-11-20 | 1978-11-20 | Turbine paragraph structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14234778A JPS5851121B2 (en) | 1978-11-20 | 1978-11-20 | Turbine paragraph structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5569703A true JPS5569703A (en) | 1980-05-26 |
| JPS5851121B2 JPS5851121B2 (en) | 1983-11-15 |
Family
ID=15313244
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14234778A Expired JPS5851121B2 (en) | 1978-11-20 | 1978-11-20 | Turbine paragraph structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5851121B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005194914A (en) * | 2004-01-05 | 2005-07-21 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing structure and turbine nozzle |
| WO2012157498A1 (en) * | 2011-05-13 | 2012-11-22 | 株式会社Ihi | Gas turbine engine |
| CN105804802A (en) * | 2016-05-18 | 2016-07-27 | 哈尔滨汽轮机厂有限责任公司 | 350 MW supercritical double-cylinder and double-exhaust steam turbine |
| FR3085055A1 (en) * | 2018-08-20 | 2020-02-21 | Safran Aircraft Engines | PIPE TRACK UPSTREAM OF A DAWN |
| JP2020139464A (en) * | 2019-02-28 | 2020-09-03 | 三菱日立パワーシステムズ株式会社 | Axial flow turbine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0322668Y2 (en) * | 1985-11-01 | 1991-05-17 |
-
1978
- 1978-11-20 JP JP14234778A patent/JPS5851121B2/en not_active Expired
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005194914A (en) * | 2004-01-05 | 2005-07-21 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing structure and turbine nozzle |
| WO2012157498A1 (en) * | 2011-05-13 | 2012-11-22 | 株式会社Ihi | Gas turbine engine |
| JP2012241520A (en) * | 2011-05-13 | 2012-12-10 | Ihi Corp | Gas turbine engine |
| US9657575B2 (en) | 2011-05-13 | 2017-05-23 | Ihi Corporation | Gas turbine engine |
| CN105804802A (en) * | 2016-05-18 | 2016-07-27 | 哈尔滨汽轮机厂有限责任公司 | 350 MW supercritical double-cylinder and double-exhaust steam turbine |
| FR3085055A1 (en) * | 2018-08-20 | 2020-02-21 | Safran Aircraft Engines | PIPE TRACK UPSTREAM OF A DAWN |
| WO2020039142A1 (en) * | 2018-08-20 | 2020-02-27 | Safran Aircraft Engines | Channelling furrow upstream of a blade |
| US11519274B2 (en) | 2018-08-20 | 2022-12-06 | Safran Aircraft Engines | Channeling furrow upstream of a blade |
| JP2020139464A (en) * | 2019-02-28 | 2020-09-03 | 三菱日立パワーシステムズ株式会社 | Axial flow turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5851121B2 (en) | 1983-11-15 |
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