US3797234A - Gas turbine system with subterranean air storage - Google Patents

Gas turbine system with subterranean air storage Download PDF

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US3797234A
US3797234A US00241299A US3797234DA US3797234A US 3797234 A US3797234 A US 3797234A US 00241299 A US00241299 A US 00241299A US 3797234D A US3797234D A US 3797234DA US 3797234 A US3797234 A US 3797234A
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air
gas turbine
hot
decompression
turbine stage
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T Schwarz
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Kraftwerk Union AG
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    • 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
    • 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
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
    • F02C1/05—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
    • F02C1/06—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy using reheated exhaust gas
    • 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

Definitions

  • the invention relates to a gas turbine system with subterranean air storage of the type which is formed of a storage cavern in a salt stratum or the like, from which combustionair stored at times of low current demand is fed to the combustion chamber of a gas turbine at times of higher current demand.
  • the stored air is subjected in such installations to fluctuating changes of state, depending on the volumetric efficiency of the storage reservoir. These changes in state occur virtually adiabatically while the reservoir is being filled and during removal of the air from the reservoir.
  • Such subterranean cavities which are produced, for example, especially in salt deposits by washing the salt out, further contain a sump formed of saturated salt water, numerous impurities partly containing silica,
  • gas turbine system with subterranean air storage space for example, in a cavern formed in a salt stratum, wherefrom combustion air stored at high pressure during periods of low output current demand from the gas turbine is fed, during periods of higher current demand, to the gas turbine combustion chamber, includes means for conducting the highly compressed stored airto a location at which it is heatable by exhaust gas of the gas turbine to a temperature below the melting temperature of any salt particles present in the stored air, and a hotair decompression turbine stage for partly decompressing the highly compressed heated stored air prior to entry of the latter into the gas turbine combustion chamber.
  • the combustion air is stored at high pressure, as noted hereinbefore.
  • the air flow is heated exclusively in surface heat exchangers by the exhaust gas heat from the gas turbine, and is then fed to the hot-air decompression turbine stage through a coarse filter.
  • the temperature of the air can be selected at about 350 C and is therefore far below the melting temperature of the salts.
  • the decompression turbine stage is mounted to particular advantage on the same shaft as that on which the associated gas turbine proper is mounted, but with a flow passage therein opposite in direction to that of the gas turbine. Moreover, both the decompression turbine stage and the gas turbine are located with a common outer casing.
  • radially disposed swirl or vortex vanes for setting the air stream into rotational flow without jolting by using the outlet energy of the discharging hotair flow, the air being deflected through an angle of 180 C and flowing around the casing of the decompression turbine stage in direction toward the gas turbine.
  • the air flow performs a torsional displacement, the helical advance of the flow being terminated by a ring-shaped partition. The'particles to be separated are removable thereat from the air flow.
  • the purified air then flows through a diffuser-like overflow tube, which surrounds the common turbine shaft from the region in which the rotational air flow is located to an antechamber located upstream of the combustion chamber.
  • FIG. 1 is a diagrammatic axial view of the gas turbine system with subterranean air storage space according to the invention.
  • FIG. 2 is a sectional view of FIG. 1 taken'along the line A-A in thedirection of the arrows.
  • FIG. 1 there is shown therein the inventive gas turbine system wherein combustion air stored at high pressure travels from a non-illustrated subterranean storage space or reservoir in a cavern of a salt stratum, for example, through a line 1 in direction of the arrow 2 and is heated in a heat exchanger 3 by the hot exhaust gas of a gas turbine 7.
  • the heated air flow is then fed through a line 4 to an air filter 5 and from there to a hot-air decompression turbine stage 6.
  • the turbine stage 6 is mounted on the same shaft 8 on which the gas turbine 7 is mounted, the shaft 8 being coupled with a shaft 9 of a generator 12.
  • the flow through the decompression turbine stage 6 is axial, in direction of the arrow 10.
  • the partially decompressed quantity of air leaving the turbine stage 6 arrives at the region of swirl or vortex vanes 14 which are secured at the end wall 13 of the casing 15, which commonly encloses both turbines 6 and 7.
  • FIG. 2 which represents a cross-sectional view taken along the line A-A in FIG. 1, the disposition of these swirl or vortex vanes 14 is shown more clearly.
  • the swirl vanes 14 set the deflected air flow into additional rotational motion virtually without jolting by using the outlet energy or velocity of the hot air flow, when the air flow passes through the annular space 29 between the outer casing 15 and the decompression turbine stage 6 in the direction of the arrow 16.
  • the helically advancing air flow produced thereby is bounded by a circular partition 17.
  • the entire or predominent part of the combustion air is conducted from the central region of the rotational air flow and directed through a diffuser 18, which extends through a central opening in the partition 17 and surrounds the turbine shaft 8, into an ante-chamber located upstream of the combustion chamber 19, in the flow direction of the combustion air.
  • the outer or marginal zone of the air flow travels axially in direction toward the partition 17, is baffled thereat and deflected radially inwardly.
  • a zone of turbulence formed thereby rotates simultaneously in the rotary direction of the main air flow set by the swirl vanes 14. Salt particles and other impurities are thereby thrown into the outer zone of the air flow and travel therewith in direction toward the partition 17.
  • suitable deflectors or baffles 20 cause a deflection into a collecting chamber 21 of the part of the air flow that is entrained or laden with impurities. Salt particles and foreign bodies thus accumulate in the collecting chamber 21.
  • the partial air flow conducted through the collecting chamber 21 is re-fed through an air filter 22 and the pipe line 23 connected thereto, into the main air flow at a suitable nonillustrated point.
  • the line 23 can, for example, discharge into the region of the cross-sectional constriction of the diffuser 18. It is, of course, also possible to discharge the partial quantity of air into the exhaust gas flue of the gas turbine, in order to have available a greater pressure difference for drawing off the impurities.
  • the combustion chamber 25 is located upstream of the gas turbine 7, which is provided with an exhaust gas channel 27 wherein the aforedescribed heat exchanger 3 is disposed.
  • the exhaust gases leave the system at lower temperature in direction of the arrow 28.
  • Gas turbine system arranged for connection to a supply of high pressure air containing salt particles for feeding said high pressure air during periods of high output current demand, comprising a gas turbine'having an exhaust means, a combustion chamber feeding hot gases to said gas turbine, a heat exchanger in said exhaust means of said gas turbine for heating said supply of high pressure air containing salt particles below the melting temperature of any salt particles present in said supply, a hot-air decompression turbine stage for reducing the pressure of the high pressure supply of air, means for delivering air from said heat exchanger to said decompression turbine stage, and means for delivering said air supply from said decompression turbine stage to said combustion chamber.
  • System according to claim 2 including a shaft disposed in said outer casing, both said hot-air decompression turbine stage and said gas turbine being mounted in common on said shaft.
  • said hot-air decompression turbine stage has a discharge end for decompressed hot air flow and including radially extending vortex vanes operative by the outlet energy of the discharging hot air flow for setting the hot air flow into rotation substantially free of jolting.
  • System according to claim 4 including an antechamber upstream of the combustion chamber in flow direction of the hot air, and a circular ring-shaped partition located between said ante-chamber and the region in which the rotational flow of the hot air is located.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • High Energy & Nuclear Physics (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

In a gas turbine system with subterranean air storage such as in a cavern formed in a salt stratum, a hot-air decompression turbine stage for partially decompressing combustion air stored at high pressure, prior to the entry thereof into the combustion chamber of the gas turbine proper, after the combustion air has been delivered by suitable conducting means to a location at which it is heated by the exhaust gases of the gas turbine to a temperature below the melting temperature of any salt particles that may be present in the stored air.

Description

United States Patent Schwarz Mar. 19, 197-4 GAS TURBINE SYSTEM WITH 3,309,867 3/1967 Ehrich 60/3909 P SUBTERRANEAN AIR STORAGE 3,616,616 11/1971 Flatt d S h E Ian 6 3,538,340 11/1970 Lang 290/52 1 W I2, I I1, [75 1 Invent c a g FOREIGN PATENTS OR APPLICATIONS 604,028 6/1948 Gre'at'Britain 60/3918 c 1 Asslgneei Kraftwerke U910" 538,956 8/1941 Great Britain 60/3918 c Aktiengesellschaft, Mulheim, Germany Primary ExaminerCarlton R. Croyle [22] Filed; AP 5 1972 Assistant Examiner-Warren Olsen Appl. No.: 241,299
Foreign Application Priority Data Apr. 6. 1971 Germany 2116851 Attorney, Agent, or FirmHerbert L. Lerner [57] ABSTRACT In a gas turbine system with subterranean air storage such as in a cavern formed in a salt stratum, a hot-air decompression turbine stage for partially decompressing combustion air stored at high pressure, prior to the entry thereof into the combustion chamber of the gas turbine proper, after the combustion air has been delivered by suitable conducting means to a location at which it is heated by the exhaust gases of the gas tur- [56] R f n Cit d bine to a temperature below the melting temperature UNITED STATES PATENTS of any salt particles that may be present in the stored 2,318,905 5/1943 Traupel 60/3918 c 3,444,672 5/1969 Alsobrooks....-. 60/3909 P 7 Claims, 2 Drawing Figures A F 27 21. A 1 PL 11.
-13 J l5 1 12 1s 19 17 29 23 21 20 GAS TURBINE SYSTEM WITH SUBTERRANEAN AIR STORAGE The invention relates to a gas turbine system with subterranean air storage of the type which is formed of a storage cavern in a salt stratum or the like, from which combustionair stored at times of low current demand is fed to the combustion chamber of a gas turbine at times of higher current demand. The stored air is subjected in such installations to fluctuating changes of state, depending on the volumetric efficiency of the storage reservoir. These changes in state occur virtually adiabatically while the reservoir is being filled and during removal of the air from the reservoir.
Such subterranean cavities, which are produced, for example, especially in salt deposits by washing the salt out, further contain a sump formed of saturated salt water, numerous impurities partly containing silica,
and insoluble rock residues. During the frequent changes in state of the air, which occur relatively rapidly, the moisture content of the air also changes. As a result of these continual changes in pressure, temperature and humidity, it must be taken into account that salt particles from the cavern will be held in suspension in the enclosed air and entrained when a large amount of the stored air is withdrawn from the cavern. When these dust particles formed primarily of sodium chloride or potassium chloride enter the gas turbine combustion chamber, they melt there and precipitate subsequently on the colder turbine blades. The deposit formed thereby can cause not only a narrowing of the gas channels in the blading and therefore produce an increased tangential loading or stress on the thrust bearing, but can also cause a reduction of power. Moreover, the salt deposit endangers the strength of the rotor blading due to intercrystalline corrosion.
The need therefore arises to free the combustion air of salt dust as completely as possible by suitable filters or dust separators prior to the entry of the air into the combustion chambers. Equipment for this purpose, which must be designed for total air through-put and the highest operating air pressure is very costly.
It is accordingly an object of the invention to provide a gas turbine system with subterranean air storage which reduces in part the technical expenditure for the apparatus which is indispensable for separating salt dust or other impurities and to use in this connection other measures which permit this reduction without exposing the gas turbine system to the dangers described hereinbefore.
With the foregoing and other objects in view, there is provided in accordance with the invention, gas turbine system with subterranean air storage space, for example, in a cavern formed in a salt stratum, wherefrom combustion air stored at high pressure during periods of low output current demand from the gas turbine is fed, during periods of higher current demand, to the gas turbine combustion chamber, includes means for conducting the highly compressed stored airto a location at which it is heatable by exhaust gas of the gas turbine to a temperature below the melting temperature of any salt particles present in the stored air, and a hotair decompression turbine stage for partly decompressing the highly compressed heated stored air prior to entry of the latter into the gas turbine combustion chamber.
The combustion air is stored at high pressure, as noted hereinbefore. When air is withdrawn, the air flow is heated exclusively in surface heat exchangers by the exhaust gas heat from the gas turbine, and is then fed to the hot-air decompression turbine stage through a coarse filter. The temperature of the air can be selected at about 350 C and is therefore far below the melting temperature of the salts.
In accordance with another feature of the invention, the decompression turbine stage is mounted to particular advantage on the same shaft as that on which the associated gas turbine proper is mounted, but with a flow passage therein opposite in direction to that of the gas turbine. Moreover, both the decompression turbine stage and the gas turbine are located with a common outer casing.
In accordance with a further feature of the invention, at the discharge end of the decompression turbine, radially disposed swirl or vortex vanes for setting the air stream into rotational flow without jolting by using the outlet energy of the discharging hotair flow, the air being deflected through an angle of 180 C and flowing around the casing of the decompression turbine stage in direction toward the gas turbine. On this path, the air flow performs a torsional displacement, the helical advance of the flow being terminated by a ring-shaped partition. The'particles to be separated are removable thereat from the air flow.
In accordance with yet another feature of the invention, the purified air then flows through a diffuser-like overflow tube, which surrounds the common turbine shaft from the region in which the rotational air flow is located to an antechamber located upstream of the combustion chamber.
Other features which are considered as characteristic for the invention are set forth in the appended claims.
Although the invention is illustrated and described herein as embodied in gas turbine system with subterranean air storage, it is nevertheless not intended to be limited to the details shown, since various modifications and structural changes may be made therein without departing from the spirit of the invention and within the scope and range of equivalents of the claims.
The construction and method of operation of the invention, however, together with additional objects and advantages thereof will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings, in which:
FIG. 1 is a diagrammatic axial view of the gas turbine system with subterranean air storage space according to the invention; and
FIG. 2 is a sectional view of FIG. 1 taken'along the line A-A in thedirection of the arrows.
Referring now to the drawing and first, particularly to FIG. 1 thereof, there is shown therein the inventive gas turbine system wherein combustion air stored at high pressure travels from a non-illustrated subterranean storage space or reservoir in a cavern of a salt stratum, for example, through a line 1 in direction of the arrow 2 and is heated in a heat exchanger 3 by the hot exhaust gas of a gas turbine 7. The heated air flow is then fed through a line 4 to an air filter 5 and from there to a hot-air decompression turbine stage 6. The turbine stage 6 is mounted on the same shaft 8 on which the gas turbine 7 is mounted, the shaft 8 being coupled with a shaft 9 of a generator 12.
The flow through the decompression turbine stage 6 is axial, in direction of the arrow 10. The partially decompressed quantity of air leaving the turbine stage 6 arrives at the region of swirl or vortex vanes 14 which are secured at the end wall 13 of the casing 15, which commonly encloses both turbines 6 and 7. In FIG. 2, which represents a cross-sectional view taken along the line A-A in FIG. 1, the disposition of these swirl or vortex vanes 14 is shown more clearly.
The swirl vanes 14 set the deflected air flow into additional rotational motion virtually without jolting by using the outlet energy or velocity of the hot air flow, when the air flow passes through the annular space 29 between the outer casing 15 and the decompression turbine stage 6 in the direction of the arrow 16.
The helically advancing air flow produced thereby is bounded by a circular partition 17. The entire or predominent part of the combustion air is conducted from the central region of the rotational air flow and directed through a diffuser 18, which extends through a central opening in the partition 17 and surrounds the turbine shaft 8, into an ante-chamber located upstream of the combustion chamber 19, in the flow direction of the combustion air.
The outer or marginal zone of the air flow travels axially in direction toward the partition 17, is baffled thereat and deflected radially inwardly. A zone of turbulence formed thereby rotates simultaneously in the rotary direction of the main air flow set by the swirl vanes 14. Salt particles and other impurities are thereby thrown into the outer zone of the air flow and travel therewith in direction toward the partition 17.
In the lower part of the partition 17 suitable deflectors or baffles 20 cause a deflection into a collecting chamber 21 of the part of the air flow that is entrained or laden with impurities. Salt particles and foreign bodies thus accumulate in the collecting chamber 21.
In order to attain a well-defined flow, the partial air flow conducted through the collecting chamber 21 is re-fed through an air filter 22 and the pipe line 23 connected thereto, into the main air flow at a suitable nonillustrated point. The line 23 can, for example, discharge into the region of the cross-sectional constriction of the diffuser 18. It is, of course, also possible to discharge the partial quantity of air into the exhaust gas flue of the gas turbine, in order to have available a greater pressure difference for drawing off the impurities.
From the ante-chamber 19 located upstream of the combustion chamber 25, the combustion air now passes through the passage 24 to the combustion chamber 25, to which fuel 26 is fed in a conventional manner shown schematically, together with the combustion air.
The combustion chamber 25 is located upstream of the gas turbine 7, which is provided with an exhaust gas channel 27 wherein the aforedescribed heat exchanger 3 is disposed. The exhaust gases leave the system at lower temperature in direction of the arrow 28.
I claim:
1. Gas turbine system arranged for connection to a supply of high pressure air containing salt particles for feeding said high pressure air during periods of high output current demand, comprising a gas turbine'having an exhaust means, a combustion chamber feeding hot gases to said gas turbine, a heat exchanger in said exhaust means of said gas turbine for heating said supply of high pressure air containing salt particles below the melting temperature of any salt particles present in said supply, a hot-air decompression turbine stage for reducing the pressure of the high pressure supply of air, means for delivering air from said heat exchanger to said decompression turbine stage, and means for delivering said air supply from said decompression turbine stage to said combustion chamber.
2. System according to claim 1 wherein said hot-air decompression turbine stage and the gas turbine are located within a common outer casing; said hot-air decompression turbine stage having a fluid flow passage therein opposite in direction to that of the gas turbine.
3. System according to claim 2 including a shaft disposed in said outer casing, both said hot-air decompression turbine stage and said gas turbine being mounted in common on said shaft.
4. System according to claim 2 wherein said hot-air decompression turbine stage has a discharge end for decompressed hot air flow and including radially extending vortex vanes operative by the outlet energy of the discharging hot air flow for setting the hot air flow into rotation substantially free of jolting.
5. System according to claim 4 including an antechamber upstream of the combustion chamber in flow direction of the hot air, and a circular ring-shaped partition located between said ante-chamber and the region in which the rotational flow of the hot air is located.
6. System according to claim 5 wherein said partition is formed with a central opening, and a diffuser-like overflow tube extends through said opening and forms a passage for air from the region in which the rotational flow thereof is located to said antechamber.
7. System according to claim 6 including a shaft disposed in said outer casing, both said decompression turbine stage and said gas turbine being mounted in common on said shaft, said diffuser-like overflow tube surrounding said common shaft.

Claims (7)

1. Gas turbine system arranged for connection to a supply of high pressure air containing salt particles for feeding said high pressure air during periods of high output current demand, comprising a gas turbine having an exhaust means, a combustion chamber feeding hot gases to said gas turbine, a heat exchanger in said exhaust means of said gas turbine for heating said supply of high pressure air containing salt particles below the melting temperature of any salt particles present in said supply, a hotair decompression turbine stage for reducing the pressure of the high pressure supply of air, means for delivering air from said heat exchanger to said decompression turbine stage, and means for delivering said air supply from said decompression turbine stage to said combustion chamber.
2. System according to claim 1 wherein said hot-air decompression turbine stage and the gas turbine are located within a common outer casing; said hot-air decompression turbine stage having a fluid flow passage therein opposite in direction to that of the gas turbine.
3. System according to claim 2 including a shaft disposed in said outer casing, both said hot-air decompression turbine stage and said gas turbine being mounted in common on said shaft.
4. System according to claim 2 wherein said hot-air decompression turbine stage has a discharge end for decompressed hot air flow and including radially extending vortex vanes operative by the outlet energy of the discharging hot air flow for setting the hot air flow into rotation substantially free of jolting.
5. System according to claim 4 including an ante-chamber upstream of the combustion chamber in flow direction of the hot air, and a circular ring-shaped partition located between said ante-chamber and the region in which the rotational flow of the hot air is located.
6. System according to claim 5 wherein said partition is formed with a central opening, and a diffuser-like overflow tube extends through said opening and forms a passage for air from the region in which the rotational flow thereof is located to said antechamber.
7. System according to claim 6 including a shaft disposed in said outer casing, both said decompression turbine stage and said gas turbine being mounted in common on said shaft, said diffuser-like overflow tube surrounding said common shaft.
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Cited By (7)

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Publication number Priority date Publication date Assignee Title
US3935469A (en) * 1973-02-12 1976-01-27 Acres Consulting Services Limited Power generating plant
US4797563A (en) * 1987-07-24 1989-01-10 Richardson Timothy M Power plant
WO2002025083A1 (en) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Two stage expansion and single stage combustion compressed air storage power plant
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
WO2012107756A1 (en) 2011-02-07 2012-08-16 Re Hydrogen Ltd High pressure hydrogen gas compressor
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
WO2020033993A1 (en) * 2018-08-17 2020-02-20 Garwoli Investments Pty Ltd Energy storage system for exhausted subsea oil and gas reservoirs

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DE2353493C3 (en) * 1973-10-25 1981-10-01 Brown, Boveri & Cie Ag, 6800 Mannheim Two- or multi-stage air storage gas turbine system
CH593423A5 (en) * 1976-03-15 1977-11-30 Bbc Brown Boveri & Cie
US4441028A (en) * 1977-06-16 1984-04-03 Lundberg Robert M Apparatus and method for multiplying the output of a generating unit

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GB604028A (en) * 1944-12-12 1948-06-28 Escher Wyss Maschf Ag Improvements in or relating to thermal power plants
US3309867A (en) * 1965-03-31 1967-03-21 Gen Electric Axial flow separator
US3444672A (en) * 1967-05-08 1969-05-20 Michigan Dynamics Inc Air cleaner for turbine engines
US3538340A (en) * 1968-03-20 1970-11-03 William J Lang Method and apparatus for generating power
US3616616A (en) * 1968-03-11 1971-11-02 Tech Dev Inc Particle separator especially for use in connection with jet engines

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GB538956A (en) * 1939-05-10 1941-08-22 Sulzer Ag Improvements in or relating to gas turbine plant
US2318905A (en) * 1939-05-10 1943-05-11 Sulzer Ag Gas turbine plant
GB604028A (en) * 1944-12-12 1948-06-28 Escher Wyss Maschf Ag Improvements in or relating to thermal power plants
US3309867A (en) * 1965-03-31 1967-03-21 Gen Electric Axial flow separator
US3444672A (en) * 1967-05-08 1969-05-20 Michigan Dynamics Inc Air cleaner for turbine engines
US3616616A (en) * 1968-03-11 1971-11-02 Tech Dev Inc Particle separator especially for use in connection with jet engines
US3538340A (en) * 1968-03-20 1970-11-03 William J Lang Method and apparatus for generating power

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3935469A (en) * 1973-02-12 1976-01-27 Acres Consulting Services Limited Power generating plant
US4797563A (en) * 1987-07-24 1989-01-10 Richardson Timothy M Power plant
WO2002025083A1 (en) * 2000-09-21 2002-03-28 Siemens Westinghouse Power Corporation Two stage expansion and single stage combustion compressed air storage power plant
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
WO2012107756A1 (en) 2011-02-07 2012-08-16 Re Hydrogen Ltd High pressure hydrogen gas compressor
WO2020033993A1 (en) * 2018-08-17 2020-02-20 Garwoli Investments Pty Ltd Energy storage system for exhausted subsea oil and gas reservoirs

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GB1374201A (en) 1974-11-20
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FR2132457B1 (en) 1975-10-24
DE2116851B2 (en) 1975-06-26
FR2132457A1 (en) 1972-11-17
LU65107A1 (en) 1972-07-12
DE2116851A1 (en) 1972-10-19
CH533764A (en) 1973-02-15
BE781556A (en) 1972-07-17

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