GB776847A - Gas-cooled gas turbine - Google Patents
Gas-cooled gas turbineInfo
- Publication number
- GB776847A GB776847A GB13847/55A GB1384755A GB776847A GB 776847 A GB776847 A GB 776847A GB 13847/55 A GB13847/55 A GB 13847/55A GB 1384755 A GB1384755 A GB 1384755A GB 776847 A GB776847 A GB 776847A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas
- gap
- labyrinth
- blades
- casing
- 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
- F01D11/001—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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
776,847. Turbines. SULZER FRERES SOC. ANON. May 13, 1955 [May 20, 1954], No. 13847/55. Class 110 (3). A multi-stage axial flow turbine in which a protective cooling gas is introduced into a labyrinth packing in the gap between the shroud ring or the equivalent of a stator blade ring and the walls of the rotor to prevent working fluid passing through the gap and to cool the surface of the rotor and in which the radial distance of the gap from the axis of the rotor is approximately the same as that of the inner ends of adjacent rotor blades has the part of the labyrinth packing lying upstream of the point of entry of the protective cooling gas arranged with a smaller resistance to flow of the cooling gas than the part downstream thereof. The hot working medium is supplied to the turbine through an annular space 1 to an annular flow channel 2. The stator guide blades 3, 4 fixed in a casing 5 have shroud rings 9 provided with labyrinth sealing rings 10 to form gaps 11, 12. Protective cooling gas which may be taken from the compressor of the gas turbine unit is led into a space 13 formed between the stator casing 5 and housing 14. A part of this gas is led to the roots of the guide blades 3 by bores 17, 18 in the casing 5. Bores 21, 22 supply another part of this air into the labyrinth gap 12. The bore 21 also constitutes a metering orifice which is so dimensioned that in normal operation a part of the protective gas issues from the gap 12 upstream of the blades 4. To maintain these conditions, the number of labyrinth rings downstream of the bore 22 is greater than the number upstream. Another part of the gas passes through a metering channel 23 into a collecting chamber 24 whence it is led through channel 25 into the labyrinth gap 11. Some of this gas passes into the working fluid upstream of the blades 3. The channels 22 and bores 23 should be distributed around the circumference of the casing.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH776847X | 1954-05-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB776847A true GB776847A (en) | 1957-06-12 |
Family
ID=4535886
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB13847/55A Expired GB776847A (en) | 1954-05-20 | 1955-05-13 | Gas-cooled gas turbine |
Country Status (2)
Country | Link |
---|---|
CH (1) | CH323720A (en) |
GB (1) | GB776847A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1126196B (en) * | 1958-11-24 | 1962-03-22 | Rolls Royce | Gas turbine jet engine with bypass compressor |
US3408044A (en) * | 1965-07-23 | 1968-10-29 | Bbc Brown Boveri & Cie | Combustion gas turbine with cooled guide vane support structure |
US3535873A (en) * | 1967-10-24 | 1970-10-27 | Joseph Szydlowski | Gas turbine cooling devices |
US4027996A (en) * | 1974-07-22 | 1977-06-07 | Kraftwerk Union Aktiengesellschaft | Turbomachine, such as a steam turbine with high steam inlet temperature, especially |
GB2119861A (en) * | 1982-05-03 | 1983-11-23 | Gen Electric | Cooling high pressure turbine blade tips in a gas turbine engine |
US11236615B1 (en) | 2020-09-01 | 2022-02-01 | Solar Turbines Incorporated | Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine |
-
1954
- 1954-05-20 CH CH323720D patent/CH323720A/en unknown
-
1955
- 1955-05-13 GB GB13847/55A patent/GB776847A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1126196B (en) * | 1958-11-24 | 1962-03-22 | Rolls Royce | Gas turbine jet engine with bypass compressor |
US3408044A (en) * | 1965-07-23 | 1968-10-29 | Bbc Brown Boveri & Cie | Combustion gas turbine with cooled guide vane support structure |
US3535873A (en) * | 1967-10-24 | 1970-10-27 | Joseph Szydlowski | Gas turbine cooling devices |
US4027996A (en) * | 1974-07-22 | 1977-06-07 | Kraftwerk Union Aktiengesellschaft | Turbomachine, such as a steam turbine with high steam inlet temperature, especially |
GB2119861A (en) * | 1982-05-03 | 1983-11-23 | Gen Electric | Cooling high pressure turbine blade tips in a gas turbine engine |
US11236615B1 (en) | 2020-09-01 | 2022-02-01 | Solar Turbines Incorporated | Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
CH323720A (en) | 1957-08-15 |
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