GB2153437A - Improvements in or relating to gas turbine power plant - Google Patents
Improvements in or relating to gas turbine power plant Download PDFInfo
- Publication number
- GB2153437A GB2153437A GB08430676A GB8430676A GB2153437A GB 2153437 A GB2153437 A GB 2153437A GB 08430676 A GB08430676 A GB 08430676A GB 8430676 A GB8430676 A GB 8430676A GB 2153437 A GB2153437 A GB 2153437A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- engine
- compressor
- casing
- gas turbine
- 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.)
- Withdrawn
Links
- 238000002485 combustion reaction Methods 0.000 claims description 15
- 239000000446 fuel Substances 0.000 claims description 9
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 238000009792 diffusion process Methods 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 27
- 238000010438 heat treatment Methods 0.000 description 3
- 238000004378 air conditioning Methods 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- 241000928624 Coula edulis Species 0.000 description 1
- 229910052581 Si3N4 Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 238000010079 rubber tapping Methods 0.000 description 1
- 230000003584 silencer Effects 0.000 description 1
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/56—Control of fuel supply conjointly with another control of the plant with power transmission control
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F02C3/103—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 the compressor being of the centrifugal 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
-
- 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
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/14—Combined heat and power generation [CHP]
Description
1
GB 2 153 437 A 1
SPECIFICATION
Improvements in or relating to gas turbine power plant
This invention relates to a gas turbine power plant 5 and is particularly though not exclusively concerned with a relatively small power plant driven by a gas turbine engine, producing electrical energy and energy for heating, refrigeration and air conditioning. Such a power plant would be useful 10 for domestic purposes, small businesses and factories.
In order for the power plant to be competitive with existing systems of domestic energy supply the gas turbine engine as well as the other components of 15 the power plant have to be relatively low in cost. The engine should thus be simple in design and have a small a number of parts as possible which are all capable of being produced by mass production methods.
20 It is an object of the present invention to provide a gas turbine engine having a small number of components which can be mass produced, the engine being reliable and capable of operation over long periods without the need of maintenance. 25 It is a further object of the invention to provide a power plant suitable for domestic or small business purposes incorporating a gas turbine engine, the power from which can be used to generate electricity, and the exhaust used for water heating, 30 room heating, air conditioning and/or refrigeration.
Accordingly the present invention provides a gas turbine engine comprising a centrifugal compressor driven by a centripetal turbine, a single counterflow combustion chamber arranged to receive a flow of 35 compressed air from the centrifugal compressor and a flow of fuel, and to discharge the products of combustion to the centripetal turbine, a relatively high inertial mass power turbine arranged to drive a load such as an a.c. generator, the power turbine 40 comprising a row of stator vanes mounted in a casing, a wall of the casing partially defining a diffusion duct into which the exhaust from the centripetal turbine is discharged, the other wall of the diffusion duct being defined by a central body of 45 the power turbine, the central body carrying a row of rotor blades located axially downstream of the stator vanes. The compressor and turbine can be mounted in a casing comprising upstream and downstream end plates between which is 50 sandwiched a central core.
The compressor casing can be at least partially defined by a surface of the upstream end plate, and the compressor exhaust volute can be defined between the upstream end plate and the central 55 core. In a preferred arrangement the compressor exhaust volute can be formed by surfaces on both the upstream plate and the central core. The turbine inlet volute can be formed by surfaces on the central core and the downstream end plate. The centripetal 60 turbine housing can be formed by a surface on the downstream end plate.
The central core preferably contains ducting from the compressor and to the turbine which terminates in a central duct and a co-axial, annular duct.
The casing component can be secured together by any suitable means, e.g. bolts or by a flanged, split ring.
An attachment spigot for the combustion chamber can be attached to the casing aligned with the termination of the ducting. The casing preferably has'a detachable intake flare, and the compressor and turbine can be attached to a common shaft journalled in a gas bearing. A gas thrust bearing can also be provided.
The stator vane casing can be attached to the turbo-compressor casing by a housing which also acts as a containment ring. The stator vanes can be attached to a ring separate from the stator vane casing, which ring can be located in a recess in the stator vane casing.
The power turbine can be mounted in gas journal and thrust bearings in an exhaust volute casing attached to the containment ring of the power turbine.
According to the present invention there is also provided a domestic energy supply comprising a gas turbine engine as outlined above, a variable frequency wide voltage regulated a.c. generator driven bythe power turbine of the engine, a boiler and/or an absorption system driven by the exhaust heat of the engine, and a control system to control the gas turbine, the electricity generated and the boiler and/or the absorption system, and to balance the energy from the electrical power output and the heat energy output.
The present invention will now be more particularly described with reference to the accompanying drawings in which
Figure 1 shows a sectional elevation of one form of gas turbine engine according to the present invention,
Figure 2 is a view on arrow A in Figure 1, including the engine combustion system in section,
Figure 3 shows in diagrammatic form a power plant incorporating a gas turbine of the type shown in Figure 1, and
Figure 4 is a notional layout of the electrical supply and control of the power plant.
Referring to Figure 1, a gas turbine engine 10 comprises a centrifugal compressor 12 driven by a centripetal turbine 14 via a shaft 16 to which the compressor and turbine are both attached. The shaft 16 is journalled in a gas bearing 18 and the rotor assembly of shaft, compressor and turbine also has a gas thrust bearing 20.
The rotor assembly is mounted in a housing 22 which comprises upstream and downstream end plates 24,26 respectively and a split central core 28 clamped between the end plates by suitable securing means, e.g. nut and bolt arrangements 30.
The upstream end plate 24 has an intake flare 32 attached to it and the inside surface of the end plate is shaped to provide the housing of the compressor 12 and partially defines the compressor outlet 34 and exhaust volute 36. The central core has a surface which in conjunction with the corresponding surfaces of the end plate defines the compressor outlet and exhaust volute.
A duct 38 is formed in the central core and
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GB 2 153 437 A 2
connects the exhaust volute 36 with a side mounted combustion chamber 39 (Figure 2).
In a similar mannerthe end plate 26 and the downstream face of the central core are shaped to define a turbine iniet volute 40 which is connected to the outlet from the combustion chamber by a duct 42 in the central core. The outlets of the ducts 38 and 42 are concentric and are attached to the combustion chamber by a suitable flanged connector 39a.
The combustion chamber 39 which is screwed to the connector 39a, has outer and inner casings 39b and 39c respectively. The inner casing has an upstream airswirler39d, and a fuel injector 39e is mounted on the outer casing and extends through the centre of the airswirler. In this instance the fuel injector as for gas fuel, but a liquid fuel or a dual fuel injector can be provided. An igniter 39f is also mounted on the outer casing, and extends through the wall of the inner casing. The inner and outer casings define an annular space 39g which receives compressed air from the duct 38. The products of combustion are discharged from the inner casing to the duct 42.
Downstream of the volute 40 and between the central core and the end plate 26 is mounted a ring of nozzle guide vanes 44 to direct the hot, high velocity gases from the combustion chamber into the turbine 14.
As well as securing the components of the rotor assembly 22 together, the securing means 30 also attach a power turbine module 46 to the rotor assembly.
The module 46 comprises two casings 48,50 which locate and retain in position the components of the module, and which are secured together by suitable clamping means (not shown). Inside the casing 48, there is located a diffuser housing 52, the internal surface of which defines the outer surface of an annular diffuser 54. The housing 52 is formed from two components, a diffuser block 56 and a ring 58 to which is attached a row of inlet guide vanes 60. The other surface defining the diffuser duct 54 is defined by the external surface of the bullet 62 of a power turbine rotor 64 on which are mounted turbine blades 66.
The power turbine rotor 64 is mounted in a gas journal bearing 68 and has a gas thrust bearing 70. Both of these bearings are located in a bearing support structure 72, contained within and held in position by the casing 50.
The exhaust gases from the power turbine pass into an exhaust duct 74 which terminates in a volute (not shown) to conduct the exhaust to atmosphere through a suitable opening (not shown) in the casing 50. The exhaust duct 74 is defined partly by the ring 58 and partly by surfaces formed on the bearing support structure 72.
The compressor, compressor driving turbine, power turbine and associated guide vanes can be made from a ceramic material, e.g. silicon nitride, or from a good quality alloy depending on the nature of the fuel used. Other components which can be made from a ceramic material are the split casing 28, the end plate 26 and the power turbine stator ring and turbine casing 58. The remaining components, particularly the containment casing 48 can be formed from steel, or a suitable metal alloy.
It will be noted that the gas turbine is made from a very small number of components which can be easily assembled either by hand or by machine.
A particular feature of the design is the multifunction capability of some of the components. For example, the bullet 62 of the power turbine also partially defines the annular diffuser duct 54, and since it will rotate at high speed wil induct a whirl velocity into the gases from the turbine 14. This feature can be used to aerodynamic advantage in the design of the power turbine and the inlet guide vanes 60. Also, the casing 48 as well as locating and retaining the diffuser duct components also acts as a containment for the power turbine in the case of turbine overspeed.
Referring to Figure 2, the gas turbine engine 10 is shown located in a silenced cabinet 76 having an intake filter and silencer 78. The power turbine 64 drives a variablefrequency wide voltage regulated a.c. generator 80, the output from which passes to a control and distribution system 82, shown in more detail in Figure 3. The exhaust from the gas turbine passes into a boiler and/or absorption system 84, and exhausts to atmosphere through a stack 86 which can be silenced.
Referring to Figure 3, the output from the a.c. generator 80 passes to a rectifier and voltage regulator 88 and hence to the domestic mains via a solid state a.c. generator 90. A tapping can be taken to charge batteries if required. A gas turbine control 92 is powered from the mains supply and receives signals inter alia from the a.c. generator to control the fuel supply to the engine by a valve 94.
Claims (12)
1. A gas turbine engine comprising a compressor driven by a turbine through a shaft, a combustion arrangement arranged to receive a flow of compressed air from the compressor and a flow of fuel, and to discharge the products of combustion to the turbine, a power turbine arranged to be driven by the exhaust from the compressor driving turbine and to drive a load, the engine comprising a plurality of components, at least two of said components partially defining the surfaces of the gas flow path through the engine, one of said surfaces being formed on a static component and the other of said surfaces being formed on a rotating component.
2. An engine as claimed in claim 1 in which the power turbine comprises at least a row of stator vanes and a row of rotor blades, the stator vanes being secured to a casing, and the rotor blades being secured to the powerturbine rotor, the exhaust from the compressor driving turbine being discharged into a diffusion duct formed by a wall of the casing and a central body of the turbine.
3. A gas turbine engine as claimed in claim 1 in which the compressor and compressor driving turbine are rotatably mounted in a casing comprising a central core and two end plates, at least one surface of the core or one of the two end
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GB 2 153 437 A 3
plates at least partially defining a surface of the compressor or compressor driving turbine.
4. An engine as claimed in claim 3 in which the casing has upstream and downstream end plates, a
5 compressor exhaust volute being defined by a surface on the upstream end plate and a surface on the core, and a turbine inlet volute defined by another surface on the core and a surface on the downstream end plate.
10 5. An engine as claimed in claim 3 in which both the compressor and compressor driving turbine have gas flow paths, the surfaces of the gas flow paths being formed by surfaces on respective bladed rotors and respective surfaces on the end
15 plates.
6. An engine as claimed in claim 3 in which the central core includes inlet ducting extending from the compressor to the combustion arrangement inlet and outlet ducting extending from the
20 combustion arrangement outlet to the compressor driving turbine inlet.
7. An engine as claimed in claim 2 in which the stator vane casing has an outer containment casing, the stator vane casing being attached to the
25 remainder of the engine by the containment casing.
8. An engine as claimed in claim 2 in which the stator vanes are secured together in a ring, and the ring of stator vanes are located in a recess formed in the stator casing.
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9. An engine as claimed in claim 1 in which the compressor comprises a centrifugal compressor, the compressor driving turbine comprises a centripetal turbine, the combustion arrangement comprises a single stage high inertial mass power
35 turbine.
10. A power plant including a gas turbine engine as claimed in claim 1, the power plant further including a variable frequency wide voltage regulated a.c. generator driven by the power turbine
40 of the engine, a boiler and/or an absorption system driven by the exhaust heat of the engine, and a control system to control the gas turbine engine, the a.c. generator and the boiler and/or the absorption system, and to heat energy output in accordance
45 with demand.
11. A gas turbine engine constructed and arranged for use and operation substantially as herein described, and with reference to Figures 1 and 2 of the accompanying drawings.
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12. A power plant, including a gas turbine engine as claimed in claim 11, constructed and arranged for use and operation substantially as herein described, and with reference to Figures 3 and 4 of the accompanying drawings.
Printed for Her Majesty's Stationery Office by Courier Press, Leamington Spa. 8/1985. Demand No. 8817443. Published by the Patent Office, 25 Southampton Buildings, London, WC2A 1AY, from which copies may be obtained.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8400356 | 1984-01-07 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8430676D0 GB8430676D0 (en) | 1985-01-16 |
| GB2153437A true GB2153437A (en) | 1985-08-21 |
Family
ID=10554670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08430676A Withdrawn GB2153437A (en) | 1984-01-07 | 1984-12-05 | Improvements in or relating to gas turbine power plant |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US4598542A (en) |
| EP (3) | EP0225868A1 (en) |
| JP (1) | JPS60156936A (en) |
| CA (1) | CA1251050A (en) |
| DE (1) | DE3483583D1 (en) |
| GB (1) | GB2153437A (en) |
| NO (1) | NO160807C (en) |
Families Citing this family (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4951460A (en) * | 1989-01-11 | 1990-08-28 | Stewart & Stevenson Services, Inc. | Apparatus and method for optimizing the air inlet temperature of gas turbines |
| GB9016353D0 (en) * | 1990-07-25 | 1990-09-12 | Csir | Power pack |
| GB2330648A (en) * | 1997-10-24 | 1999-04-28 | Robert Pickering | Domestic boiler heated by gas turbine |
| AU2088599A (en) * | 1997-12-19 | 1999-07-12 | Allied-Signal Inc. | An uninterruptible microturbine power generating system |
| JP2001527180A (en) | 1997-12-20 | 2001-12-25 | アライド・シグナル・インコーポレーテツド | Control of constant internal temperature of turbine in power generation system of microturbine |
| ES2248967T3 (en) * | 1999-06-09 | 2006-03-16 | Alliedsignal Inc. | MICROTURBINE ENERGY GENERATOR SYSTEM. |
| SE521955C2 (en) * | 2000-05-30 | 2003-12-23 | Turbec Ab | Integrated gas compressor |
| US6622489B1 (en) | 2000-10-25 | 2003-09-23 | Hybrid Power Generation Systems, Llc | Integrated gas booster modulation control method |
| US6513318B1 (en) | 2000-11-29 | 2003-02-04 | Hybrid Power Generation Systems Llc | Low emissions gas turbine engine with inlet air heating |
| US6571563B2 (en) | 2000-12-19 | 2003-06-03 | Honeywell Power Systems, Inc. | Gas turbine engine with offset shroud |
| US6536217B2 (en) | 2000-12-20 | 2003-03-25 | Honeywell Power Systems Inc. | Liquid fuel reverse purge |
| GB2373299B (en) * | 2001-03-12 | 2004-10-27 | Alstom Power Nv | Re-fired gas turbine engine |
| AU2003290874A1 (en) * | 2002-11-15 | 2004-06-15 | Sprint Communications Company L.P. | Proton exchange membrane based power system for a telecommunication facility |
| US6960838B2 (en) * | 2002-11-15 | 2005-11-01 | Sprint Communications Company L.P. | Power system for a telecommunication facility |
| US6930402B1 (en) * | 2003-05-15 | 2005-08-16 | Sprint Communications Company L.P. | Power system for a telecommunication facility |
| US7456513B2 (en) * | 2002-11-15 | 2008-11-25 | Sprint Communications Company L.P. | Modular cell site with air-turbine backup |
| DE502004011691D1 (en) * | 2003-11-04 | 2010-11-04 | Mann & Hummel Gmbh | ORIGINAL SPIRAL CHANNEL |
| US7081687B2 (en) * | 2004-07-22 | 2006-07-25 | Sprint Communications Company L.P. | Power system for a telecommunications facility |
| US7615889B2 (en) * | 2005-05-02 | 2009-11-10 | Sprint Communications Company L.P. | Modular cell site |
| US9142844B2 (en) | 2005-05-18 | 2015-09-22 | Sprint Communications Company L.P. | Power system for a telecommunications network |
| US20060263656A1 (en) * | 2005-05-18 | 2006-11-23 | Sprint Communications Company L.P. | Power system with reformer |
| US7370666B2 (en) * | 2005-09-14 | 2008-05-13 | Sprint Communications Company L.P. | Power system with computer-controlled fuel system |
| US7557531B2 (en) * | 2005-12-19 | 2009-07-07 | Sprint Communications Company L.P. | Power system utilizing flow batteries |
| CN102434217A (en) * | 2011-11-01 | 2012-05-02 | 哈尔滨东安发动机（集团）有限公司 | Integrated cantilever rotor structure |
| WO2014130159A1 (en) | 2013-02-23 | 2014-08-28 | Ottow Nathan W | Blade clearance control for gas turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB866969A (en) * | 1959-12-14 | 1961-05-03 | George Colville Best | Gas turbine engines |
| GB1027530A (en) * | 1964-03-02 | 1966-04-27 | Vlastimir Davidovic | Gas turbine cycle improvement |
| US4118927A (en) * | 1975-12-05 | 1978-10-10 | United Turbine Ab & Co. Kommanditbolag | Gas turbine power plant |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1002293A (en) * | 1946-09-03 | 1952-03-04 | Rateau Soc | Gas turbine installation for combined heat and power production and control of this installation |
| US2709893A (en) * | 1949-08-06 | 1955-06-07 | Laval Steam Turbine Co | Gas turbine power plant with heat exchanger and cooling means |
| US2709889A (en) * | 1951-06-22 | 1955-06-07 | Wadsworth W Mount | Gas turbine using revolving ram jet burners |
| GB723368A (en) * | 1952-06-23 | 1955-02-09 | Rover Co Ltd | Vehicle gas turbines |
| GB756413A (en) * | 1954-10-08 | 1956-09-05 | David Dutton Budworth | Improvements in or relating to the supply and the combustion of fuel in gas turbines |
| US2923526A (en) * | 1955-03-31 | 1960-02-02 | Gen Electric | Turbine |
| US2944785A (en) * | 1955-05-18 | 1960-07-12 | Thompson Ramo Wooldridge Inc | Impeller for turbine engine and the like |
| US2821067A (en) * | 1956-05-28 | 1958-01-28 | Boeing Co | Combustion chamber construction in a gas turbine engine |
| CH359929A (en) * | 1957-10-01 | 1962-01-31 | Bbc Brown Boveri & Cie | Gas turbine for ship propulsion |
| US2946192A (en) * | 1958-05-16 | 1960-07-26 | Standard Motor Co Ltd | Gas turbine power plant |
| US3187188A (en) * | 1959-07-21 | 1965-06-01 | Curtiss Wright Corp | High speed turbo-generator |
| FR1254037A (en) * | 1960-02-29 | 1961-02-17 | Sulzer Ag | Radial turbine for compressible media |
| DE1426265A1 (en) * | 1962-03-12 | 1968-12-19 | Volvo Ab | Gas turbine plant |
| US3422800A (en) * | 1967-06-19 | 1969-01-21 | Gen Electric | Combined gas turbine and waste heat boiler control system |
| GB1315307A (en) * | 1969-08-21 | 1973-05-02 | Cav Ltd | Turbo superchargers for internal combustion engines |
| US3751886A (en) * | 1971-08-31 | 1973-08-14 | Westinghouse Electric Corp | Vertical steam drum |
| DE2165528A1 (en) * | 1971-12-30 | 1973-07-12 | Kloeckner Humboldt Deutz Ag | DEVICE FOR CREATING A SMALL GAP BETWEEN THE ROTATING SHOVELS AND THE WALL OF A FLOW MACHINE |
| FR2197420A5 (en) * | 1972-08-25 | 1974-03-22 | Cav Ltd | |
| FR2264972B1 (en) * | 1974-03-20 | 1977-06-17 | Turbine Ind | |
| US4076452A (en) * | 1974-04-09 | 1978-02-28 | Brown, Boveri-Sulzer Turbomaschinen Ag | Gas turbine plant |
| US4009568A (en) * | 1975-10-30 | 1977-03-01 | General Motors Corporation | Turbine support structure |
| DE2706110C3 (en) * | 1977-02-14 | 1981-07-09 | Aktiengesellschaft Kühnle, Kopp & Kausch, 6710 Frankenthal | Compressor housing preferably for exhaust gas turbochargers |
| DE2941252A1 (en) * | 1979-10-11 | 1981-05-07 | Joachim Dr. 7031 Aidlingen Artmann | De-centralised electric power and heating plant - uses gas turbine to drive power generator and hot exhaust gases for heating purposes |
| SE423741B (en) * | 1980-09-29 | 1982-05-24 | Motor Turbine & Transmissions | GAS TURBINE MACHINERY, SPECIAL FOR VEHICLE OPERATION |
-
1984
- 1984-12-05 EP EP87100279A patent/EP0225868A1/en not_active Withdrawn
- 1984-12-05 DE DE8787100280T patent/DE3483583D1/en not_active Expired - Fee Related
- 1984-12-05 GB GB08430676A patent/GB2153437A/en not_active Withdrawn
- 1984-12-05 EP EP84308462A patent/EP0148590B1/en not_active Expired
- 1984-12-05 EP EP87100280A patent/EP0227638B1/en not_active Expired
- 1984-12-13 US US06/681,258 patent/US4598542A/en not_active Expired - Fee Related
- 1984-12-27 JP JP59281882A patent/JPS60156936A/en active Granted
-
1985
- 1985-01-04 NO NO850046A patent/NO160807C/en unknown
- 1985-01-04 CA CA000471504A patent/CA1251050A/en not_active Expired
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB866969A (en) * | 1959-12-14 | 1961-05-03 | George Colville Best | Gas turbine engines |
| GB1027530A (en) * | 1964-03-02 | 1966-04-27 | Vlastimir Davidovic | Gas turbine cycle improvement |
| US4118927A (en) * | 1975-12-05 | 1978-10-10 | United Turbine Ab & Co. Kommanditbolag | Gas turbine power plant |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3483583D1 (en) | 1990-12-13 |
| NO850046L (en) | 1985-07-08 |
| EP0225868A1 (en) | 1987-06-16 |
| NO160807C (en) | 1989-05-31 |
| EP0148590A3 (en) | 1985-11-21 |
| NO160807B (en) | 1989-02-20 |
| EP0227638A1 (en) | 1987-07-01 |
| GB8430676D0 (en) | 1985-01-16 |
| EP0148590A2 (en) | 1985-07-17 |
| JPH0580571B2 (en) | 1993-11-09 |
| JPS60156936A (en) | 1985-08-17 |
| EP0148590B1 (en) | 1989-04-12 |
| CA1251050A (en) | 1989-03-14 |
| US4598542A (en) | 1986-07-08 |
| EP0227638B1 (en) | 1990-11-07 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |