GB191210179A - Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids. - Google Patents
Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids.Info
- Publication number
- GB191210179A GB191210179A GB191210179DA GB191210179A GB 191210179 A GB191210179 A GB 191210179A GB 191210179D A GB191210179D A GB 191210179DA GB 191210179 A GB191210179 A GB 191210179A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbines
- pumps
- liquids
- arrangement
- clearance losses
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
10,179. Holzer, H. May 4, 1911, [Convention date]. Blades.-In turbines the clearances around the the shrouds d, Fig. 1, of blades l, f are formed with inclined passages a', a<2>, b', b<2>. The static pressure differences tend to cause leakage past the shrouds from left to right, while the flow of the fluid creates a suction at a' and b<2> and a pressure at a<2> and b<2>, thereby creating a tendency for back leakage. The clearance losses are consequently neutralized or minimized.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE191210179X | 1911-05-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB191210179A true GB191210179A (en) | 1912-06-20 |
Family
ID=32337206
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB191210179D Expired GB191210179A (en) | 1911-05-04 | 1912-04-30 | Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids. |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB191210179A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3011762A (en) * | 1956-03-28 | 1961-12-05 | Pouit Robert | Turbines and in particular gas turbines |
| US3640638A (en) * | 1969-07-02 | 1972-02-08 | Rolls Royce | Axial flow compressor |
| FR2559218A1 (en) * | 1984-02-06 | 1985-08-09 | Gen Electric | AXIAL COMPRESSOR MUNIED IN ITS ENCLOSURE ENCLOSURE REDUCING DAWN LOSSES |
| US4645417A (en) * | 1984-02-06 | 1987-02-24 | General Electric Company | Compressor casing recess |
| US4738586A (en) * | 1985-03-11 | 1988-04-19 | United Technologies Corporation | Compressor blade tip seal |
| EP0528138A1 (en) * | 1991-08-08 | 1993-02-24 | Asea Brown Boveri Ag | Blade shroud for axial turbine |
| EP0536575A1 (en) * | 1991-10-08 | 1993-04-14 | Asea Brown Boveri Ag | Shroud band for axial flow turbine |
| WO2005061854A1 (en) * | 2003-12-17 | 2005-07-07 | Watson Cogeneration Company | Gas turbine tip shroud rails |
| WO2011157927A1 (en) | 2010-06-17 | 2011-12-22 | Snecma | Compressor and turbomachine with optimized efficiency |
| EP3276129A1 (en) * | 2016-07-25 | 2018-01-31 | United Technologies Corporation | Rotor blade for a gas turbine engine including a contoured tip |
-
1912
- 1912-04-30 GB GB191210179D patent/GB191210179A/en not_active Expired
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3011762A (en) * | 1956-03-28 | 1961-12-05 | Pouit Robert | Turbines and in particular gas turbines |
| US3640638A (en) * | 1969-07-02 | 1972-02-08 | Rolls Royce | Axial flow compressor |
| FR2559218A1 (en) * | 1984-02-06 | 1985-08-09 | Gen Electric | AXIAL COMPRESSOR MUNIED IN ITS ENCLOSURE ENCLOSURE REDUCING DAWN LOSSES |
| US4606699A (en) * | 1984-02-06 | 1986-08-19 | General Electric Company | Compressor casing recess |
| US4645417A (en) * | 1984-02-06 | 1987-02-24 | General Electric Company | Compressor casing recess |
| US4738586A (en) * | 1985-03-11 | 1988-04-19 | United Technologies Corporation | Compressor blade tip seal |
| EP0528138A1 (en) * | 1991-08-08 | 1993-02-24 | Asea Brown Boveri Ag | Blade shroud for axial turbine |
| US5238364A (en) * | 1991-08-08 | 1993-08-24 | Asea Brown Boveri Ltd. | Shroud ring for an axial flow turbine |
| EP0536575A1 (en) * | 1991-10-08 | 1993-04-14 | Asea Brown Boveri Ag | Shroud band for axial flow turbine |
| WO2005061854A1 (en) * | 2003-12-17 | 2005-07-07 | Watson Cogeneration Company | Gas turbine tip shroud rails |
| WO2011157927A1 (en) | 2010-06-17 | 2011-12-22 | Snecma | Compressor and turbomachine with optimized efficiency |
| US20130156559A1 (en) * | 2010-06-17 | 2013-06-20 | Snecma | Compressor and a turbine engine with optimized efficiency |
| US9488179B2 (en) * | 2010-06-17 | 2016-11-08 | Snecma | Compressor and a turbine engine with optimized efficiency |
| EP3276129A1 (en) * | 2016-07-25 | 2018-01-31 | United Technologies Corporation | Rotor blade for a gas turbine engine including a contoured tip |
| US10808539B2 (en) | 2016-07-25 | 2020-10-20 | Raytheon Technologies Corporation | Rotor blade for a gas turbine engine |
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