GB853314A - Improvements in or relating to axial flow turbo-machines such as turbines or compressors - Google Patents
Improvements in or relating to axial flow turbo-machines such as turbines or compressorsInfo
- Publication number
- GB853314A GB853314A GB3050756A GB3050756A GB853314A GB 853314 A GB853314 A GB 853314A GB 3050756 A GB3050756 A GB 3050756A GB 3050756 A GB3050756 A GB 3050756A GB 853314 A GB853314 A GB 853314A
- Authority
- GB
- United Kingdom
- Prior art keywords
- extensions
- blade
- extension
- blades
- members
- 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.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
853,314. Turbine and compressor blades. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Aug. 30, 1957 [Oct. 5, 1956], No. 30507/56. Class 110 (3). In an axial-flow turbine or compressor having shrouded blades, each blade has an extension or extensions which projects or project beyond the shroud in a direction away from the working portion of the blade, the extension or extensions carrying two segmental blocks, at least one of which has sealing means arranged to co-operate with a part of the machine with which the blades are relatively rotatable, the segmental blocks and the blade extension or extensions being shaped to interlock. In a first embodiment, the blades 1 are of aerofoil profile and have root portions 15, the opposite ends of the blades being formed with dovetailshaped extensions 2 which are passed through openings 4 in shroud members 3, the shrouds abutting against shoulders formed on the blades. Pairs of segmental members 5, 6 are clamped by means of bolts 8 to the blade extensions 2, the members 5, 6 having grooves which together correspond to the dovetail shape of the extensions 2. The members 5, 6 are provided with fins 7 which co-operate with the adjacent surface of the rotor to provide a seal. A plurality of parts 5, 6 are provided so as to afford a substantially continuous ring member.. In Fig. 4 the blade tip is shaped to provide a dovetail-shaped groove 12, the blade tip being passed through an opening in a shroud member 9. Two wedge-shaped members 10 are held against the sides of the groove 12 by means of a wedge-shaped key member 14 which is urged towards the bottom of the groove 12 by means of a bolt 13 engaging with the shroud 9. Sealing fins 11 are provided on the wedge members 10. In Fig. 5, the blade is formed integral with a shroud 18 and dovetail-shaped extension 19, pairs of segmental parts 20 which are grooved to correspond to the dovetail extension 19 being clamped to the extension by screws 21. Sealing fins 22 are provided on the segmental parts 20.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3050756A GB853314A (en) | 1956-10-05 | 1956-10-05 | Improvements in or relating to axial flow turbo-machines such as turbines or compressors |
| FR1183012D FR1183012A (en) | 1956-10-05 | 1957-10-02 | Improvements to axial turbo-machines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3050756A GB853314A (en) | 1956-10-05 | 1956-10-05 | Improvements in or relating to axial flow turbo-machines such as turbines or compressors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB853314A true GB853314A (en) | 1960-11-02 |
Family
ID=10308766
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3050756A Expired GB853314A (en) | 1956-10-05 | 1956-10-05 | Improvements in or relating to axial flow turbo-machines such as turbines or compressors |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR1183012A (en) |
| GB (1) | GB853314A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
| US4884820A (en) * | 1987-05-19 | 1989-12-05 | Union Carbide Corporation | Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members |
| US4889470A (en) * | 1988-08-01 | 1989-12-26 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
| DE102009042029A1 (en) * | 2009-09-17 | 2011-03-24 | Mtu Aero Engines Gmbh | Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction |
| CN110761848A (en) * | 2019-12-16 | 2020-02-07 | 中国船舶重工集团公司第七0三研究所 | Gas compressor stator blade ring of gas turbine |
| DE102018213983A1 (en) * | 2018-08-20 | 2020-02-20 | MTU Aero Engines AG | Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine |
| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4834613A (en) * | 1988-02-26 | 1989-05-30 | United Technologies Corporation | Radially constrained variable vane shroud |
| US7329096B2 (en) * | 2005-10-18 | 2008-02-12 | General Electric Company | Machine tooled diaphragm partitions and nozzles |
-
1956
- 1956-10-05 GB GB3050756A patent/GB853314A/en not_active Expired
-
1957
- 1957-10-02 FR FR1183012D patent/FR1183012A/en not_active Expired
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3079128A (en) * | 1961-01-23 | 1963-02-26 | Burge Joseph | Sealing and securing means for turbomachine blading |
| US4884820A (en) * | 1987-05-19 | 1989-12-05 | Union Carbide Corporation | Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members |
| US4889470A (en) * | 1988-08-01 | 1989-12-26 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
| DE102009042029A1 (en) * | 2009-09-17 | 2011-03-24 | Mtu Aero Engines Gmbh | Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction |
| DE102018213983A1 (en) * | 2018-08-20 | 2020-02-20 | MTU Aero Engines AG | Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine |
| US11300004B2 (en) | 2018-08-20 | 2022-04-12 | MTU Aero Engines AG | Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine |
| CN110761848A (en) * | 2019-12-16 | 2020-02-07 | 中国船舶重工集团公司第七0三研究所 | Gas compressor stator blade ring of gas turbine |
| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| CN112324520B (en) * | 2020-10-27 | 2022-08-30 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| FR1183012A (en) | 1959-07-02 |
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