US3733820A - Combustion gas generator - Google Patents
Combustion gas generator Download PDFInfo
- Publication number
- US3733820A US3733820A US00133321A US3733820DA US3733820A US 3733820 A US3733820 A US 3733820A US 00133321 A US00133321 A US 00133321A US 3733820D A US3733820D A US 3733820DA US 3733820 A US3733820 A US 3733820A
- Authority
- US
- United States
- Prior art keywords
- gas generator
- spiral
- generator according
- combustion chamber
- combustion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C15/00—Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
-
- 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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/10—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
Definitions
- ABSTRACT A combustible mixture of air and fuel is provided to a chamber formed in a housing; the combustion chamber is of a specific shape, so arranged that, in longitudinal section, it has approximately the shape of a single turn spiral, with the fuel and supply means connected to the spiral at the point of the maximum rate of change of curvature of the spiral wall, and the outlet from the spiral being located such that its axis is shifted with respect to the location of maximum rate of change of curvature of the spiral, by an angle of over 180 and less than 300, and preferably between 200 and 235, for example about 217; upon admission of pre-heated air and fuel, self-ignition will occur providing combustion gases in shock wave or surges.
- the present invention relates to a combustion gas generator, and more particularly to an apparatus to provide high-temperature gases, from which energy can be extracted, which are generated by self-ignition in a combustion chamber to provide shock waves, or surges of the hot gases.
- Combustion gas, or hot gas generators are known; in previous constructions, a longitudinal combustion tube has been provided in which pulsating combustion sequences occur, ignition of the combustible mixture being obtained by periodic pressure variations occurring within the tube itself.
- Such hot gas generators have not found favorable acceptance because the thermal efficiency thereof is low, and because other technical difficulties in maintenance and construction inhibited wide use.
- a housing defines a combustion chamber which, in longitudinal cross-section is approximately in the form of a single turn spiral.
- the supply for fuel and air is located at the point of highest rate of change of curvature of the spiral, and the axis of the outlet tube from the spiral is located with respect to the air and fuel inlets into the spiral-shaped chamber, that is, to the point at greatest rate of change of the spiral, offset by an angle of more than 180, but less than 300, for example within 200235.
- FIG. 1 is a longitudinal sectional view through the apparatus
- FIG. 2 is a transverse sectional view along lines IIII of FIG. 1.
- the apparatus is used to provide hot gases, for example to drive gas turbines, stationary or vehicular drive apparatus or flow machines, or it can be used to provide hot gases for reaction propulsion, for example for aviation use.
- It is essentially formed of a housing made ofa material which is highly heat-resistant, such as steel castings, light metal castings or the like.
- the housing is formed of two essentially symmetrical half-elements, to be interconnected in rigid, and gas-tight manner.
- the interior of the housing 1 is formed with a combustion chamber 2, having a longitudinal or plan outline in the form of a single-turn spiral, as seen in FIG. 1.
- a second outer wall 12 Spaced from wall 8 is a second outer wall 12 which is likewise approximately semi-circularly shaped, to de fine between walls 8 and 12 a chamber which is separated by a separating ring 13 into two chamber parts 14, 15. Both of the chamber parts 14, 15 surround the combustion chamber 2 from the outside and provide for pre-heating of the gas to be supplied to the combustion chamber.
- the gas itself is provided to the combustion chamber from a compressor, or supercharger 16 at some small pressure, with respect to ambient air pressure; this gas, typically air, is supplied to the combustion chamber 2 at the specific location of the maximum rate of change of curvature 3.
- the compressor or supercharger 16 can be of any known construction.
- Compressor or supercharger 16 can be secured to the housing 1 by means of a somewhat tangentially projecting rod 24.
- Rod 24 is located in the interior, preferably coaxial, with a tubular fresh air duct 26 which communicates with the suction side of the compressor 16.
- Compressor 16 if constructed in accordance with the aforementioned application, reverses the flow of air being compressed and supplies compressed air, in counterflow, to the combustion apparatus as indicated by arrows C, and C
- the compressed fresh air is directed about the outside of the inlet duct 26 and supplied through duct 28 into chambers 14, 15.
- the compressor itself can be driven independently; in accordance with a preferred form of the invention, the compressor is driven by means of a portion of the hot gases derived directly from the combustion apparatus.
- a portion of the outlet 7 is separated, for example as schematically indicated at 7', FIGS. 1, 2, to direct hot gases to a turbine wheel connected to a rotating structure within compressor 16; about 10-15 percent of the hot gases generated in the gas generator of FIGS. 1 and 2 are suitably conducted to a turbine T to drive the compressor.
- Other compressors than that described in the application can be used, for example axial flow compressors or fans supplying air at an elevated pressure level to the combustion chamber.
- Fuel such as gasoline, benzine, kerosene, or the like, or other inexpensive liquid fuel is supplied byv a pair of parallel tubes 5. These tubes 5 are located partly, at least, within the interior of chambers l4, in order to preheat the fuel being supplied (omitted from FIG. 2 for clarity).
- a nozzle 30, forming a carburetor or spray or atomizer end is located at the terminal end of tube 5 which, as noted, is placed at. the point of maximum curvature 3 of the spiral.
- Nozzle preferably includes a small conical element inserted into tube 5, and pointed inwardly, and having a small opening at the tip thereof, to provide good spray and atomization of fuel derived from fuel line 5.
- the amount of hot gases generated, or the gas pressure, respectively, within the combustion chamber 2 can be controlled by means of an eccentric element 31 located immediately adjacent point 3.
- the inner wall portion, close to point 3, is swingably mounted over a pivot 38, the position of the pivot being controlled by an eccentric element 31. Changing the position of the wall portion between the end of the wall and the remainder of the wall by swinging about swing point 38 changes the pressure distribution and thus the quantity of the hot gases generated within the chamber and removed through outlet 7.
- the transition point from chamber 2 to the outlet tube 7 is rounded, as at 34, so that as little additional turbulence is introduced as possible, and so that the flow through the outlet tube will be as little turbulent as can be obtained.
- the diametrically opposite tip of the outlet tube 7 is extended into a somewhat spoonshaped projection 35. Projection extends into the outlet tube 7 and further contributes to directing a major portion of the pressure waves arising within chamber 2 into the outlet tube 7.
- This dead space 40 arises due to the U-bend in the shaped wall 8.
- the dead space 40 is closed off by a plate member 36.
- Hot energy-supplying gases are generated by supplying from compressor 16 fresh air into chambers 14, 15, with a slight amount of pressure above atmospheric.
- Theair while being supplied through chambers 14, 15, is preheated.
- This pre-heated air being supplied to the terminal end 4, terminating in the combustion chamher, carries fuel from nozzle 30, in finely atomized form, into the combustion chamber.
- the quantity of air and fuel is selected to be an explosive mixture.
- This explosive mixture is highly subject to self-ignition; upon ignition, an explosion-like shock wave will occur within the combustion chamber 2, which propagates itself at the radially outer wall of the chamber 2, that is, along the inner side of wall 8.
- This shock wave or surge propagates in the progressive, circular eddy and the shock wave travels in the direction towards the outlet 7.
- a pump (not shown) supplies a little amount of fuel to chambers 14, 15, which fuel is ignited so that heat will be generated within chambers 14, 15.
- Generation of heat causes a comparatively small amount of air to move in the direction of the jump at the rate of curvature 3 which will carry along fuel from fuel pipe 5.
- This fuel already has been preheated due to heat exchange with the heated air in chambers 14, 15.
- sufficient fuel is ejected from nozzle 5 so that the air-fuel mixture is of the proper ratio, and as the pressure wave builds up within the chamber, an initial spontaneous ignition will result and an initial cycle, as above described, will occur.
- subsequent ignition cycles follow automatically, without the addition of auxiliary fuel into chambers 14, 15, to heat the air therein so long as sufficient fuel is supplied through supply pipe 5 to chamber 2.
- said fuel supply means comprises a fuel supply line (5), said line being located at least in part in at least one of said preheat chambers to pre-heat fuel being supplied to said combustion chamber.
- Gas generator according to claim 1 in combination with an air compressor (16) wherein the housing of the combustion gas generator and said air compressor are rigidly interconnected.
- said compressor is a rotatable compressor, adapted to be driven by heated combustion gases, said compressor being interconnected (7') with the outlet (7) to receive part of the combustion gases from said generator to drive said compressor;
- said compressor is of the type receiving and delivering air in counterflow direction.
- Gas generator according to claim 1 wherein the chamber, in transverse section, has an outer region which is approximately circular.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH565270A CH540429A (de) | 1970-04-16 | 1970-04-16 | Einrichtung zur Erzeugung von Treibgas |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3733820A true US3733820A (en) | 1973-05-22 |
Family
ID=4297156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US00133321A Expired - Lifetime US3733820A (en) | 1970-04-16 | 1971-04-12 | Combustion gas generator |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US3733820A (de) |
| CH (1) | CH540429A (de) |
| DE (1) | DE2118039A1 (de) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150285506A1 (en) * | 2012-10-12 | 2015-10-08 | King Abdullah University Of Science And Technology | Standing detonation wave engine |
-
1970
- 1970-04-16 CH CH565270A patent/CH540429A/de not_active IP Right Cessation
-
1971
- 1971-04-12 US US00133321A patent/US3733820A/en not_active Expired - Lifetime
- 1971-04-14 DE DE19712118039 patent/DE2118039A1/de active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150285506A1 (en) * | 2012-10-12 | 2015-10-08 | King Abdullah University Of Science And Technology | Standing detonation wave engine |
| US9841192B2 (en) * | 2012-10-12 | 2017-12-12 | King Abdullah University Of Science And Technology | Standing detonation wave engine |
Also Published As
| Publication number | Publication date |
|---|---|
| DE2118039A1 (de) | 1971-10-28 |
| CH540429A (de) | 1973-08-15 |
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