GB809957A - Improvements in two-shaft gas turbine installations - Google Patents
Improvements in two-shaft gas turbine installationsInfo
- Publication number
- GB809957A GB809957A GB26017/55A GB2601755A GB809957A GB 809957 A GB809957 A GB 809957A GB 26017/55 A GB26017/55 A GB 26017/55A GB 2601755 A GB2601755 A GB 2601755A GB 809957 A GB809957 A GB 809957A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- heat exchanger
- compressor
- tubes
- axis
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
809,957. Gas turbine plant. HENSCHEL & SOHN G.m.b.H. Sept. 12, 1955 [Sept. 10, 1954], No. 26017/55. Class 110 (3). [Also in Groups XII and XIII] A gas turbine plant comprising a turbine driving at least one compressor, an effective power turbine and a heat exchanger having inlet and outlet drums connected by tubes in which the power turbine exhaust gases heat the air delivered by the compressor by passing over the tubes in a direction substantially at right angles to their longitudinal axis, has the compressor-turbine set disposed below the heat exchanger so that its axis runs parallel to the axes of the heat exchanger tubes or the heat exchanger drums while the axis of the effective power turbine runs in a horizontal plane at right angles to the axis of the turbine compressor set. Air compressed in a compressor 15 passes through an intercooler 16 to a compressor 17 which discharges through a pipe 18 to the upper drum 1 of a heat exchanger. The air passes through the tubes 3 where it is heated by the exhaust gases of the useful power turbine 9 to the lower drum 2 which incorporates a combustion chamber 4. The combustion gases from this chamber pass to a turbine 7, which drives the compressors 15, 17, and then through a conduit 8 to a useful power turbine 9 which discharges through a duct 10 into the heat exchanger. A reheat combustion chamber may be incorporated in the conduit 8. The gases flow in three cross currents 11, 12, 13 through the heat exchanger and pass to atmosphere through the duct 14. The lower drum 2 is rigidly mounted and the upper drum 1 is free so as to follow the expansion of the tubes 3. The upper drum 1 may be supported by anchors which are situated in the gas current beside the heat exchanger tubes 3. Expansion joints 19, 22 are provided in the ducts 6, 18. To prevent movement of these ducts due to expansion transmitting stresses to the turbinecompressor set, the ducts 6, 18 are rigidly connected to the drum 2 by brackets 20, 21. The turbine-compressor set may be supported by the lower drum 2. To shorten the length of the connecting ducts the axis of the turbinecompressor set is arranged in the plane of the heat exchanger and the axis of the useful power turbine is arranged at right angles to this plane. In a modification, the drums 1, 2 are arranged vertically with the axes of the drums adjacent the compressor discharge and turbine inlet respectively.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE809957X | 1954-09-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB809957A true GB809957A (en) | 1959-03-04 |
Family
ID=6723440
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB26017/55A Expired GB809957A (en) | 1954-09-10 | 1955-09-12 | Improvements in two-shaft gas turbine installations |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB809957A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1375866A3 (en) * | 2002-06-26 | 2005-09-28 | General Electric Company | Inlet bleed heater for heating inlet air to a compressor and methods of fabricating and transporting the heater |
-
1955
- 1955-09-12 GB GB26017/55A patent/GB809957A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1375866A3 (en) * | 2002-06-26 | 2005-09-28 | General Electric Company | Inlet bleed heater for heating inlet air to a compressor and methods of fabricating and transporting the heater |
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