CA2105692A1 - Gas turbine group - Google Patents
Gas turbine groupInfo
- Publication number
- CA2105692A1 CA2105692A1 CA002105692A CA2105692A CA2105692A1 CA 2105692 A1 CA2105692 A1 CA 2105692A1 CA 002105692 A CA002105692 A CA 002105692A CA 2105692 A CA2105692 A CA 2105692A CA 2105692 A1 CA2105692 A1 CA 2105692A1
- Authority
- CA
- Canada
- Prior art keywords
- fluid
- combustion chamber
- flow engine
- flow
- 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.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
-
- 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
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
-
- 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
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
Abstract
ABSTRACT OF THE DISCLOSURE
In a gas turbine group, the combustion chamber is placed embodied as an annular combustion chamber (1) between two fluid-flow engines (2, 3). In the normal case, the fluid-flow engine (2) located upstream of the annular combustion chamber (1) is a compressor (2b) and the fluid-flow engine (3) located downstream of the annular combustion chamber (1) is a turbine. The fluid-flow engine located downstream of the annular combus-tion chamber (1) in this case has no first row of guide blades, but its blading begins immediately with a row (6) of turbine blades. The latter is subjected to the swirl from the fluid-flow engine (2) located upstream of the annular combustion chamber (1). The swirl itself is conserved over the entire length of the annular combustion chamber (1), it being the case that owing to the swirl the gas flow executes a helical motion in the axial flow direction of the annular combustion chamber (1).
(sole figure)
In a gas turbine group, the combustion chamber is placed embodied as an annular combustion chamber (1) between two fluid-flow engines (2, 3). In the normal case, the fluid-flow engine (2) located upstream of the annular combustion chamber (1) is a compressor (2b) and the fluid-flow engine (3) located downstream of the annular combustion chamber (1) is a turbine. The fluid-flow engine located downstream of the annular combus-tion chamber (1) in this case has no first row of guide blades, but its blading begins immediately with a row (6) of turbine blades. The latter is subjected to the swirl from the fluid-flow engine (2) located upstream of the annular combustion chamber (1). The swirl itself is conserved over the entire length of the annular combustion chamber (1), it being the case that owing to the swirl the gas flow executes a helical motion in the axial flow direction of the annular combustion chamber (1).
(sole figure)
Description
TITLE OF THE INV~NTION
Gas turbine group BACKGROUND OF THE INVENTION
Field of the Invention The present invention relates to a gas turbine group in accordance with the preamble of claim 1.
Discussion of sackqround In the design of the newer combustion chamber generation, for example as an annular combustion chamber, the aim is to minimize the overall length so far as thereby to achieve as high a shaft stability as possible. However, it is found immediately given this minimization that too short a time interval is avail-able per se for the required burn up rate, with the result that such a design is attended by decisive disadvantages with respect to the efficiency and to the emission of pollutants.
SUMMARY OF THE INVENTION
Accordingly, the object of this invention, as it is defined in the claims, is to maximize the dwell time of the gas particles in the combustion chamber in a gas turbine group of the type mentioned at the beginning, without decisively changing the configura-tion of the combustion chamber in the process.
A longer dwell time of the gas particles may be achieved in conjunction with the stipulation of a minimized length of the effective combustion chamber by imposing on the gas flow a helical swirling motion which by comparison with a motion in which the gas particles pass straight through the combustion chamber entails a decisive lengthening of the transit time.
In order to achieve such a motion, it is proposed that the outlet swirl from the fluid-flow engine connected upstream of the combustion chamber not be neutralized by a row of reguiding blades acting there, but that it be transferred into the combustion chamber and, if required, that it even be intensified.
The essential advantages of the invention are to be seen in that fir~tly the last row of reguiding blades of the fluid-flow engine acting upstream of the .
210~692 combustion chamber i 8 eliminated. It is achieved as a result that the existing swirling motion in this fluid-flow engine, prescribed by the last row of turbine blades of the fluid-flow engine acting upstream of the combustion chamber, is transferred into the combustion chamber and is continued there helically in conjunction with the same velocity vector and maintained in such a way that advantages result therefrom with regard to burn up rate and the emission of pollutants.
It is, of cour~e, also possible for the blades which produce the swirling motion to be placed directly upstream of the combustion chamber, something which appears to be indicated in the case of conventional gas turbine groups.
A further advantage of the invention is to be seen in that the first row of guide blades of the fluid-flow engine connected downstream of the combustion chamber is entirely eliminated, because the conditions for the inlet of the gas flow into the first row of turbine blades of this fluid-flow engine are fulfilled by the swirling motion in the combustion chamber.
A further advantage of the invention is to be seen in that the relocation of the swirl generator from a hotter site located downstream of the combustion chamber to a cooler site located upstream of the same entails a significant reduction in the cooling air consumption, and this has an extremely positive effect on the efficiency of the installation, because higher ISO temperatures are thereby possible for the same hot gas temperature.
A further advantage of the invention is to be seen in that the approach flow of the first row of turbine blades of the fluid-flow engine connected downstream of the combustion chamber is more uniform.
Advantageous and expedient developments of the achievement of the object according to the invention are defined in the dependent claim~.
. - .
.. ~ . .. . -:
Gas turbine group BACKGROUND OF THE INVENTION
Field of the Invention The present invention relates to a gas turbine group in accordance with the preamble of claim 1.
Discussion of sackqround In the design of the newer combustion chamber generation, for example as an annular combustion chamber, the aim is to minimize the overall length so far as thereby to achieve as high a shaft stability as possible. However, it is found immediately given this minimization that too short a time interval is avail-able per se for the required burn up rate, with the result that such a design is attended by decisive disadvantages with respect to the efficiency and to the emission of pollutants.
SUMMARY OF THE INVENTION
Accordingly, the object of this invention, as it is defined in the claims, is to maximize the dwell time of the gas particles in the combustion chamber in a gas turbine group of the type mentioned at the beginning, without decisively changing the configura-tion of the combustion chamber in the process.
A longer dwell time of the gas particles may be achieved in conjunction with the stipulation of a minimized length of the effective combustion chamber by imposing on the gas flow a helical swirling motion which by comparison with a motion in which the gas particles pass straight through the combustion chamber entails a decisive lengthening of the transit time.
In order to achieve such a motion, it is proposed that the outlet swirl from the fluid-flow engine connected upstream of the combustion chamber not be neutralized by a row of reguiding blades acting there, but that it be transferred into the combustion chamber and, if required, that it even be intensified.
The essential advantages of the invention are to be seen in that fir~tly the last row of reguiding blades of the fluid-flow engine acting upstream of the .
210~692 combustion chamber i 8 eliminated. It is achieved as a result that the existing swirling motion in this fluid-flow engine, prescribed by the last row of turbine blades of the fluid-flow engine acting upstream of the combustion chamber, is transferred into the combustion chamber and is continued there helically in conjunction with the same velocity vector and maintained in such a way that advantages result therefrom with regard to burn up rate and the emission of pollutants.
It is, of cour~e, also possible for the blades which produce the swirling motion to be placed directly upstream of the combustion chamber, something which appears to be indicated in the case of conventional gas turbine groups.
A further advantage of the invention is to be seen in that the first row of guide blades of the fluid-flow engine connected downstream of the combustion chamber is entirely eliminated, because the conditions for the inlet of the gas flow into the first row of turbine blades of this fluid-flow engine are fulfilled by the swirling motion in the combustion chamber.
A further advantage of the invention is to be seen in that the relocation of the swirl generator from a hotter site located downstream of the combustion chamber to a cooler site located upstream of the same entails a significant reduction in the cooling air consumption, and this has an extremely positive effect on the efficiency of the installation, because higher ISO temperatures are thereby possible for the same hot gas temperature.
A further advantage of the invention is to be seen in that the approach flow of the first row of turbine blades of the fluid-flow engine connected downstream of the combustion chamber is more uniform.
Advantageous and expedient developments of the achievement of the object according to the invention are defined in the dependent claim~.
. - .
.. ~ . .. . -:
2~5~9~
BRIEF DESCRIPTION OF THE DRAWINGS
A more complete appreciation of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawing of an exemplary embodiment of the invention, wherein all the elements not required for the immediate under-standing of the invention are omitted, the flow direction of the medium is specified by arrows, and the sole figure shows diagrammatically a typical annular combustion chamber having fluid-flow engines connected upstream and downstream.
DESCRIPTION OF THE_PREFERRED EMBODIMENTS
Referring now to the drawing, the annular combustion chamber 1 represented in the figure extends between a first fluid-flow engine 2, connected upstream, and a second fluid-flow engine 3, connected downstream. The fluid-flow engines 2, 3 and the annular combustion chamber 1 are preferably situated on a common rotor shaft 11. As to the nature of the first fluid-flow engine 2, the latter can be a compressor 2b of a gas turbine group or, for example, a high-pressure gas turbine of a power station installation, for example a combined installation. The fluid-flow engine 3 located downstream of the annular combustion chamber 1 i8 a gas turbine, for example a high-pressure or low-pressure turbine. The length of the combustion chamber 1 is maximized per se in the light of the available space, in order likewise to maximize the dwell time of the gas particles, it being the case that, as will further be set forth later, a helical swirling motion is prescribed in the combustion cham~er, starting from the fluid-flow engine 2. After the last row 5 of turbine blades in the fluid-flow engine 2, a row 4 of reguiding blades is provided only if required, firstly independently of whether this fluid-flow engine 2 is a compressor or a turbine. This row 4 of reguiding blade~
is always eliminated when the gas flow is released from ... ~
210~692 the last row 5 of turbine blades of the fluid-flow engine 2 with an adequately strong swirl into the annular combustion chamber 1. Consequently, the optionally provided row 4 of reguiding blades in the fluid-flow engine 2 is used, as may be necessary, to intensify the swirl so that it is present at an adequate strength over the entire length of the annular combustion chamber 1. Owing to the swirl, the gas flow executes a helical motion 12 in the axial flow direction 9 of the annular combustion chamber 1 in such a way that the distance covered by each ga~ particle between the first fluid-flow engine 2 and the second fluid-flow engine 3 is longer than if the gas flow were to traverse the annular combustion chamber 1 in a purely axial fashion, it being necessary to take into account that the flow velocity occurring in the case of axial traversal is as far as possible not exceeded in the case of the helical flow, and this requires a larger combustion chamber flow cross-section. It should be pointed out in addition that the swirling motion has a positive effect with regard to intensive mixing with the fuel 10 injected into the annular combustion chamber 1 directly downstream of the first fluid-flow engine 2. The fluid-flow engine connected downstream of the annular combustion chamber 1 no longer has a first row of guide blades at its inlet, but begins with a row 6 of turbine blades. Subsequently, the fluid-flow engine 3 is conventionally constructed as a turbine, that is to say there follow a row 7 of guide blades, row 8 of turbine blades, etc. Owing to the relocation of the swirl generator for the fluid-flow engine 3 downstream of the annular combustion chamber 1 at a site upstream of the same, there is a significant effect on the cooling air consumption. Due to the fact that the swirl generator now acts at a site of lower temperature, the cooling air consumption is minimized.
As a result, higher ISO temperatures are possible for the same hot gas temperature. A possibility of permitting the swiri strength to increase given a 21~S692 constant rate of flow consists in providing the annular combustion cham~er 1 with a mean radius which is degressive in the flow direction, that is to say to configure the annular combustion chamber 1 conically in the flow direction with respect to the central axis 13 of the engine in conjunction with the same flow cross section. If a diffuser is provided for hydrodynamic reasons after a first fluid-flow engine, it is preferable to provide the row 4 of reguiding blades after said diffuser.
Obviously, numerous modifications and varia-tions of the present invention are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as speci-fically described herein.
. , .
., ~ , .
-,
BRIEF DESCRIPTION OF THE DRAWINGS
A more complete appreciation of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawing of an exemplary embodiment of the invention, wherein all the elements not required for the immediate under-standing of the invention are omitted, the flow direction of the medium is specified by arrows, and the sole figure shows diagrammatically a typical annular combustion chamber having fluid-flow engines connected upstream and downstream.
DESCRIPTION OF THE_PREFERRED EMBODIMENTS
Referring now to the drawing, the annular combustion chamber 1 represented in the figure extends between a first fluid-flow engine 2, connected upstream, and a second fluid-flow engine 3, connected downstream. The fluid-flow engines 2, 3 and the annular combustion chamber 1 are preferably situated on a common rotor shaft 11. As to the nature of the first fluid-flow engine 2, the latter can be a compressor 2b of a gas turbine group or, for example, a high-pressure gas turbine of a power station installation, for example a combined installation. The fluid-flow engine 3 located downstream of the annular combustion chamber 1 i8 a gas turbine, for example a high-pressure or low-pressure turbine. The length of the combustion chamber 1 is maximized per se in the light of the available space, in order likewise to maximize the dwell time of the gas particles, it being the case that, as will further be set forth later, a helical swirling motion is prescribed in the combustion cham~er, starting from the fluid-flow engine 2. After the last row 5 of turbine blades in the fluid-flow engine 2, a row 4 of reguiding blades is provided only if required, firstly independently of whether this fluid-flow engine 2 is a compressor or a turbine. This row 4 of reguiding blade~
is always eliminated when the gas flow is released from ... ~
210~692 the last row 5 of turbine blades of the fluid-flow engine 2 with an adequately strong swirl into the annular combustion chamber 1. Consequently, the optionally provided row 4 of reguiding blades in the fluid-flow engine 2 is used, as may be necessary, to intensify the swirl so that it is present at an adequate strength over the entire length of the annular combustion chamber 1. Owing to the swirl, the gas flow executes a helical motion 12 in the axial flow direction 9 of the annular combustion chamber 1 in such a way that the distance covered by each ga~ particle between the first fluid-flow engine 2 and the second fluid-flow engine 3 is longer than if the gas flow were to traverse the annular combustion chamber 1 in a purely axial fashion, it being necessary to take into account that the flow velocity occurring in the case of axial traversal is as far as possible not exceeded in the case of the helical flow, and this requires a larger combustion chamber flow cross-section. It should be pointed out in addition that the swirling motion has a positive effect with regard to intensive mixing with the fuel 10 injected into the annular combustion chamber 1 directly downstream of the first fluid-flow engine 2. The fluid-flow engine connected downstream of the annular combustion chamber 1 no longer has a first row of guide blades at its inlet, but begins with a row 6 of turbine blades. Subsequently, the fluid-flow engine 3 is conventionally constructed as a turbine, that is to say there follow a row 7 of guide blades, row 8 of turbine blades, etc. Owing to the relocation of the swirl generator for the fluid-flow engine 3 downstream of the annular combustion chamber 1 at a site upstream of the same, there is a significant effect on the cooling air consumption. Due to the fact that the swirl generator now acts at a site of lower temperature, the cooling air consumption is minimized.
As a result, higher ISO temperatures are possible for the same hot gas temperature. A possibility of permitting the swiri strength to increase given a 21~S692 constant rate of flow consists in providing the annular combustion cham~er 1 with a mean radius which is degressive in the flow direction, that is to say to configure the annular combustion chamber 1 conically in the flow direction with respect to the central axis 13 of the engine in conjunction with the same flow cross section. If a diffuser is provided for hydrodynamic reasons after a first fluid-flow engine, it is preferable to provide the row 4 of reguiding blades after said diffuser.
Obviously, numerous modifications and varia-tions of the present invention are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as speci-fically described herein.
. , .
., ~ , .
-,
Claims (8)
1. A gas turbine group, consisting of a first and a second fluid-flow engine and of at least one combustion chamber connected therebetween, wherein the second fluid-flow engine has no first row of guide blades, and the first row of guide blades of the second fluid-flow engine can be subjected to the swirl from the first fluid-flow engine.
2. The gas turbine group as claimed in claim 1, wherein the first fluid-flow engine is a compressor and the second fluid-flow engine is a turbine.
3. The gas turbine group as claimed in claim 1, wherein the first fluid-flow engine and the second fluid-flow engine are turbines.
4. The gas turbine group as claimed in one of claims 1-3, wherein the intensification and/or direction of the swirl of the last row of turbine blades of the first fluid-flow engine can be achieved by means of a row of reguiding blades connected downstream of said row of turbine blades.
5. The gas turbine group as claimed in claims 1-4, wherein the combustion chamber is an annular combustion chamber which extends axially or quasi-axially between the first and second fluid-flow engine.
6. The gas turbine group as claimed in claim 5, wherein the annular combustion chamber has a degressive mean radius in the flow direction in conjunction with the same flow cross section.
7. The gas turbine group as claimed in claims 1-4, wherein the combustion chamber consists of one or more annularly arranged combustion chambers, which are arranged between the first and the second fluid-flow engine in such a way that the swirl formed in the first fluid-flow engine is maintained until being applied to the second fluid-flow engine.
8. The gas turbine group as claimed in claim 7, wherein a plurality of individual combustion chambers arranged on the circumference have a helical configuration for the purpose of transmitting swirl.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEP4232383.5 | 1992-09-26 | ||
| DE4232383A DE4232383A1 (en) | 1992-09-26 | 1992-09-26 | Gas turbine group |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2105692A1 true CA2105692A1 (en) | 1994-03-27 |
Family
ID=6468967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002105692A Abandoned CA2105692A1 (en) | 1992-09-26 | 1993-09-08 | Gas turbine group |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0590297A1 (en) |
| JP (1) | JPH06193461A (en) |
| KR (1) | KR940007348A (en) |
| CA (1) | CA2105692A1 (en) |
| DE (1) | DE4232383A1 (en) |
| PL (1) | PL300467A1 (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19507763A1 (en) * | 1995-03-06 | 1996-09-12 | Siemens Ag | Method and device for burning a fuel in a gas turbine |
| DE19541303A1 (en) * | 1995-11-06 | 1997-05-28 | Siemens Ag | Gas turbine arrangement e.g.for driving electrical power generators |
| DE19641725A1 (en) * | 1996-10-10 | 1998-04-16 | Asea Brown Boveri | Gas turbine with sequential combustion |
| DE59710046D1 (en) | 1997-03-20 | 2003-06-12 | Alstom Switzerland Ltd | Gas turbine with a toroidal combustion chamber |
| GB2349671A (en) * | 1999-04-26 | 2000-11-08 | Andrew David James Sampson | Gas turbine having rotating mixing chambers and helical flow |
| KR20010085016A (en) * | 2001-07-18 | 2001-09-07 | 이재창 | Jet engine using exhaust gas |
| FR2888631B1 (en) * | 2005-07-18 | 2010-12-10 | Snecma | TURBOMACHINE WITH ANGULAR AIR DISTRIBUTION |
| WO2007102807A1 (en) * | 2006-03-06 | 2007-09-13 | United Technologies Corporation | Angled flow annular combustor for turbine engine |
| EP1995433A1 (en) | 2007-05-24 | 2008-11-26 | Siemens Aktiengesellschaft | Gas turbo group and method for controlling a gas turbo group |
| EP2808611B1 (en) | 2013-05-31 | 2015-12-02 | Siemens Aktiengesellschaft | Injector for introducing a fuel-air mixture into a combustion chamber |
| EP2808612A1 (en) | 2013-05-31 | 2014-12-03 | Siemens Aktiengesellschaft | Gas turbine combustion chamber with tangential late lean injection |
| EP2808610A1 (en) | 2013-05-31 | 2014-12-03 | Siemens Aktiengesellschaft | Gas turbine combustion chamber with tangential late lean injection |
| US11434831B2 (en) | 2018-05-23 | 2022-09-06 | General Electric Company | Gas turbine combustor having a plurality of angled vanes circumferentially spaced within the combustor |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE847091C (en) * | 1944-05-13 | 1952-08-21 | Daimler Benz Ag | Hot air jet engine |
| US2627719A (en) * | 1947-06-13 | 1953-02-10 | Edward A Stalker | Gas turbine combustion chamber having controlled laminar flow of air for combustion and insulation |
| US2755623A (en) * | 1953-02-19 | 1956-07-24 | Ferri Antonio | Rotating flow combustor |
| DE1035306B (en) * | 1953-02-26 | 1958-07-31 | Schoppe Fritz | Process for mixing gaseous, liquid or solid substances as well as for the production of reaction products and device for carrying out the process |
| US3088281A (en) * | 1956-04-03 | 1963-05-07 | Bristol Siddeley Engines Ltd | Combustion chambers for use with swirling combustion supporting medium |
| US3342280A (en) * | 1957-04-04 | 1967-09-19 | Hovercraft Dev Ltd | Jet sheet enclosure for compressed gases |
| DE1145438B (en) * | 1958-12-15 | 1963-03-14 | Bristol Siddeley Engines Ltd | Burning device |
| DE1818595U (en) * | 1959-05-11 | 1960-09-22 | Entwicklungsbau Pirna Veb | COMBUSTION CHAMBER FOR GAS TURBINES. |
| CH398182A (en) * | 1962-11-14 | 1965-08-31 | Saurer Ag Adolph | Gas turbine plant |
| GB1069033A (en) * | 1965-01-30 | 1967-05-17 | Rolls Royce | Improvements in or relating to gas turbine jet propulsion engines |
| GB1127660A (en) * | 1966-09-17 | 1968-09-18 | Rolls Royce | Gas turbine jet propulsion engine |
| US3738105A (en) * | 1971-06-24 | 1973-06-12 | Avco Corp | Gas turbine engine structure |
| US3859786A (en) * | 1972-05-25 | 1975-01-14 | Ford Motor Co | Combustor |
| FR2446384A1 (en) * | 1979-01-15 | 1980-08-08 | Simon Jean | TURBOMACHINE |
| DD142082A5 (en) * | 1979-02-16 | 1980-06-04 | Combustion Equip Ass | BURNER |
| DE2918328A1 (en) * | 1979-05-07 | 1980-11-13 | Herbert Borreck | Rotating gas turbine engine - has combustion chamber revolving with compressor and turbine with rotating casing common to all |
| DE3117515C2 (en) * | 1980-05-07 | 1983-11-10 | Brown, Boveri & Cie Ag, 6800 Mannheim | Overflow housing |
| CH679799A5 (en) * | 1988-07-25 | 1992-04-15 | Christian Reiter | |
| US5025622A (en) * | 1988-08-26 | 1991-06-25 | Sol-3- Resources, Inc. | Annular vortex combustor |
-
1992
- 1992-09-26 DE DE4232383A patent/DE4232383A1/en not_active Withdrawn
-
1993
- 1993-08-23 EP EP93113414A patent/EP0590297A1/en not_active Withdrawn
- 1993-09-08 CA CA002105692A patent/CA2105692A1/en not_active Abandoned
- 1993-09-23 PL PL93300467A patent/PL300467A1/en unknown
- 1993-09-24 JP JP5237976A patent/JPH06193461A/en not_active Withdrawn
- 1993-09-25 KR KR1019930019760A patent/KR940007348A/en not_active Application Discontinuation
Also Published As
| Publication number | Publication date |
|---|---|
| PL300467A1 (en) | 1994-04-05 |
| JPH06193461A (en) | 1994-07-12 |
| DE4232383A1 (en) | 1994-03-31 |
| EP0590297A1 (en) | 1994-04-06 |
| KR940007348A (en) | 1994-04-27 |
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