JPS5523320A - Blade coupling structure for axial-flow turbo-machine - Google Patents
Blade coupling structure for axial-flow turbo-machineInfo
- Publication number
- JPS5523320A JPS5523320A JP9451978A JP9451978A JPS5523320A JP S5523320 A JPS5523320 A JP S5523320A JP 9451978 A JP9451978 A JP 9451978A JP 9451978 A JP9451978 A JP 9451978A JP S5523320 A JPS5523320 A JP S5523320A
- Authority
- JP
- Japan
- Prior art keywords
- blades
- machine
- projections
- blade
- caused
- 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.)
- Pending
Links
Abstract
PURPOSE: To provide a blade coupling structure for turbo-machine, which is capable of minimizing vibrational force acted to the blades as small as possible and reducing loss due to leakage of working fluid from top end portions of blades to a considerable extent, by attaining the same structural strength as can be obtained by a unitrary structure of blades without restricting tolerance in the strength of material against thermal stress.
CONSTITUTION: At the top end portion of blade 11 on both of upper and lower surfaces thereof, there is formed a projection 12 which extends perpendicularly to the length of blade 11. Along the marginal portion on the front side of porjection 12, there is formed a groove 13a, whereas a projection 13b is formed on the back side. These grooves 13a and projections 13b are coupled together in assembling the blades in the manner that a required amount of clearance is left between them. In operation of the machine, thermal expansion is caused at first at projections 12 and at the portion of blades where high-temperature fluid is passed. However, excessive stress is not caused since grooves 13a and projections 13b are coupled together with an appropriate circumferential spacing. Further, thermal contraction is not caused almost at all, at the time of stopping operation of the machine or when load is lowered abruptly.
COPYRIGHT: (C)1980,JPO&Japio
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9451978A JPS5523320A (en) | 1978-08-04 | 1978-08-04 | Blade coupling structure for axial-flow turbo-machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9451978A JPS5523320A (en) | 1978-08-04 | 1978-08-04 | Blade coupling structure for axial-flow turbo-machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5523320A true JPS5523320A (en) | 1980-02-19 |
Family
ID=14112567
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9451978A Pending JPS5523320A (en) | 1978-08-04 | 1978-08-04 | Blade coupling structure for axial-flow turbo-machine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5523320A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3802741A1 (en) * | 1988-01-30 | 1989-08-03 | Asea Brown Boveri | METHOD FOR TENSIONING BLADES |
| US5842831A (en) * | 1996-04-19 | 1998-12-01 | Asea Brown Boveri Ag | Arrangement for the thermal protection of a rotor of a high-pressure compressor |
| US6439844B1 (en) * | 2000-12-11 | 2002-08-27 | General Electric Company | Turbine bucket cover and brush seal |
| EP1408199A1 (en) * | 2002-10-08 | 2004-04-14 | United Technologies Corporation | Leak resistant vane cluster |
| US6877956B2 (en) * | 2002-12-23 | 2005-04-12 | General Electric Company | Methods and apparatus for integral radial leakage seal |
| US20130089424A1 (en) * | 2011-10-07 | 2013-04-11 | Mtu Aero Engines Gmbh | Blade row for a turbomachine |
-
1978
- 1978-08-04 JP JP9451978A patent/JPS5523320A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3802741A1 (en) * | 1988-01-30 | 1989-08-03 | Asea Brown Boveri | METHOD FOR TENSIONING BLADES |
| US4884951A (en) * | 1988-01-30 | 1989-12-05 | Asea Brown Boveri Ltd. | Method of clamping blades |
| DE3802741C2 (en) * | 1988-01-30 | 1997-02-13 | Asea Brown Boveri | Method of bracing blades |
| US5842831A (en) * | 1996-04-19 | 1998-12-01 | Asea Brown Boveri Ag | Arrangement for the thermal protection of a rotor of a high-pressure compressor |
| US6439844B1 (en) * | 2000-12-11 | 2002-08-27 | General Electric Company | Turbine bucket cover and brush seal |
| EP1408199A1 (en) * | 2002-10-08 | 2004-04-14 | United Technologies Corporation | Leak resistant vane cluster |
| WO2004033871A2 (en) * | 2002-10-08 | 2004-04-22 | United Technologies Corporation | Leak resistant vane cluster |
| US6910854B2 (en) | 2002-10-08 | 2005-06-28 | United Technologies Corporation | Leak resistant vane cluster |
| WO2004033871A3 (en) * | 2002-10-08 | 2009-04-23 | United Technologies Corp | Leak resistant vane cluster |
| US6877956B2 (en) * | 2002-12-23 | 2005-04-12 | General Electric Company | Methods and apparatus for integral radial leakage seal |
| US20130089424A1 (en) * | 2011-10-07 | 2013-04-11 | Mtu Aero Engines Gmbh | Blade row for a turbomachine |
| US9441490B2 (en) * | 2011-10-07 | 2016-09-13 | Mtu Aero Engines Gmbh | Blade row for a turbomachine |
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