GB647406A - Improvements in gas turbines - Google Patents
Improvements in gas turbinesInfo
- Publication number
- GB647406A GB647406A GB34381/47A GB3438147A GB647406A GB 647406 A GB647406 A GB 647406A GB 34381/47 A GB34381/47 A GB 34381/47A GB 3438147 A GB3438147 A GB 3438147A GB 647406 A GB647406 A GB 647406A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- speed
- shaft
- nozzles
- inlet
- 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
- 239000000446 fuel Substances 0.000 abstract 7
- 238000002485 combustion reaction Methods 0.000 abstract 5
- 230000001105 regulatory effect Effects 0.000 abstract 5
- 238000012856 packing Methods 0.000 abstract 1
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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/055—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor being of the positive-displacement type
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- 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
- F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
- F02C6/16—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads for storing compressed air
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/16—Mechanical energy storage, e.g. flywheels or pressurised fluids
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
647,406. Gas turbine plant. TERCE, P. J. J. Dec. 29, 1947, No. 34381. Convention date, Feb. 23. 1945. [Class 110(iii)] [Also in Group XXIX] A gas turbine plant is arranged for providing the same useful power at four different operating speeds. The bladed rotor drives the air-compressors and one fuel pump for the combustion chamber. The oppositely-rotating stator provides the useful power and drives a second fuel pump. Power is transferred from the bladed rotor system to the useful power system by means of a motor driven by the excess air delivered by the compressors. Change from one speed to another and to an idling speed is effected by simultaneous regulation of the air inlets to the compressors and the fuel supply from the pump driven from the useful power shaft. The fuel supply from the other pump is regulated to maintain constant the pressure of the compressed-air supply. There are two compressors in parallel. The inlet to one of them has only two settings : a full opening for all the four operating speeds and a fully throttled opening for idling speed. The inlet to the other is fully throttled for both the top speed and the idling speed and has a progressively increasing opening for the other speeds, with the largest opening for the lowest. The gas turbine comprises a bladed rotor 4 mounted on a shaft 5 and an oppositely-rotating casing 1, carrying nozzles 2 and exhaust passages, mounted on a useful power shaft 3. The casing is coupled directly to a combustion chamber 6 with a labyrinth packing 26. Fuel is supplied to the combustion chamber through nozzles 10, 11 by pumps 12, 13. The pump 12 is driven from the shaft 3 and the pump 13 from the shaft 5. Combustion air is compressed in pumps 15, which may be in two stages with intercooling, driven from the shaft 5. There are two pumps 15, operating in parallel but with different regulation. The air is delivered to a reservoir 14, and passes to the combustion chamber and to an air motor 18 which is drivingly connected with the shaft 3. The air from the pumps 15 passes through an exhaust gas heat-exchanger (not shown) which is located within the reservoir 14. The delivery of fuel to nozzles 11 is regulated by means of an escape pipe 33 which is opened by a pressure-responsive device 22 when the pressure in the reservoir 14 rises. The delivery of fuel to nozzles 10 is regulated by means of an escape pipe 51 the opening to which is controlled by a speed-responsive device 23 driven from the shaft 3. The device includes a five-stepped obturator valve 53, Fig. 7, co-operating with an orifice 52. Each of four of the steps corresponds to one of the four operating speeds. At the idling speed the largest part is at the orifice. One of the air pumps 15 has its inlet regulated by a two-stepped obturator valve controlled by a speed-responsive device 24 driven by the shaft 3. The inlet is fully open for the four operating speeds and is throttled at the idling speed. The inlet to the other air pump is regulated by a four-stepped valve, controlled by the device 24, which substantially closes the inlet for both top speed and idling speed, opens it fully for the lowest speed and closes it in steps for the higher speeds. The turbine nozzles are divided into two groups; one group for use at the four operating speeds and the other for idling. Each nozzle is supplied from a separate chamber in the rotating casing. The entry to each of the chambers supplying the normal turbine nozzles is governed by a ball valve 71, Fig. 11, in a chamber 67 having an outlet, 56 and an inlet 69 in a wall having a number of slots 70, Fig. 12. At idling speed, the flow of gas through slots 70 carries the ball 71 to the outlet 56 which it closes. At operating speeds, the ball is carried by centrifugal force to the position shown. The entry to each of the chambers supplying the idling speed nozzles is governed by a ball 66, Fig. 10, in a radially positioned chamber 62 in the casing. At idling speed, the ball is on the seat 65 and the passage to the chamber from 60 by pipes 63 is open. At operating speeds the ball moves under centrifugal force to the radially outer seat 64 and closes the passage. At the same time the auxiliary nozzles are connected to atmosphere past the seating 64 in less than that of seating 65 so as to provide a greater seating area on which the gas pressure acts.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR647406X | 1945-02-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB647406A true GB647406A (en) | 1950-12-13 |
Family
ID=9002075
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB34381/47A Expired GB647406A (en) | 1945-02-23 | 1947-12-29 | Improvements in gas turbines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB647406A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1251256A1 (en) * | 2001-04-17 | 2002-10-23 | Heinz Dipl.-Ing. Fehrs | Gas turbine |
-
1947
- 1947-12-29 GB GB34381/47A patent/GB647406A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1251256A1 (en) * | 2001-04-17 | 2002-10-23 | Heinz Dipl.-Ing. Fehrs | Gas turbine |
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