GB925113A - Improvements relating to gas-turbine power plant - Google Patents
Improvements relating to gas-turbine power plantInfo
- Publication number
- GB925113A GB925113A GB3879461A GB3879461A GB925113A GB 925113 A GB925113 A GB 925113A GB 3879461 A GB3879461 A GB 3879461A GB 3879461 A GB3879461 A GB 3879461A GB 925113 A GB925113 A GB 925113A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft portion
- extension
- compressor
- turbine
- hollow
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
925,113. Gas turbine plant. DAIMLER-BENZ A.G. Oct. 30, 1961 [Nov. 9, 1960], No. 38794/61. Class 110 (3). [Also in Group XXIV] A compressor drive-shaft arrangement for a gas turbine power plant comprises at least three bearings and two shaft portions, for the turbine and compressor rotors, respectively, which are centred one through the other and are coupled together as regards rotation and which, on the final assembly of the shaft, are releasably connected together axially on the compressor side and accessibly from the outside. A hollow compressor shaft portion V 2 receives an extension T 2 <SP>1</SP> of a turbine shaft portion T 2 , which extension is provided with an internal thread into which is screwed a bolt 25 by means of a long box spanner. The bolt has a collar 25<SP>1</SP> which tightens a disc 26 against a step 23 in the hollow shaft portion and the end face of the extension to provide an axial abutment. A locking sleeve 27, is pressed against the collar 25<SP>1</SP> by a short bolt or plug 28 screwed into an internal thread in the end of the compressor shaft portion. The turbine and compressor shaft portions are splined together at 20<SP>1</SP> and are centred at 21. During operation, a thrust exerted on the shaft portion T 2 in the direction of arrow Y is transmitted by way of abutment 23, 26 to the shaft portion V 2 which is subjected to a larger thrust in the direction of arrow X. The thrust difference is taken by a bearing 11. In an alternative embodiment, the extension projects right through the hollow shaft portion. An externally threaded portion on the end of the extension protrudes from the hollow shaft portion and is provided with a nut which tightens a flanged sleeve against a shoulder on the extension and the end face of the hollow shaft portion, to provide the abutment. The extension is provided with an intermediate expansible portion of reduced area.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DED34694A DE1162635B (en) | 1960-11-09 | 1960-11-09 | Gas turbine engine with runner in three bearings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB925113A true GB925113A (en) | 1963-05-01 |
Family
ID=7042294
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3879461A Expired GB925113A (en) | 1960-11-09 | 1961-10-30 | Improvements relating to gas-turbine power plant |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE1162635B (en) |
| GB (1) | GB925113A (en) |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH248083A (en) * | 1945-03-03 | 1947-04-15 | Sulzer Ag | Rotor for turbo machines. |
| BE541298A (en) * | 1954-11-27 |
-
1960
- 1960-11-09 DE DED34694A patent/DE1162635B/en active Pending
-
1961
- 1961-10-30 GB GB3879461A patent/GB925113A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| DE1162635B (en) | 1964-02-06 |
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