US3685294A

US3685294A - Hot gas pumps and thrusters

Info

Publication number: US3685294A
Application number: US34257A
Authority: US
Inventors: Daniel E Nelson
Original assignee: Individual
Current assignee: Individual
Priority date: 1970-05-04
Filing date: 1970-05-04
Publication date: 1972-08-22
Anticipated expiration: 1989-08-22

Abstract

This is a hot gas dredger or pump in which compressed air is mixed with fuel and ignited in a combustor near the end of a tube into which hot gases from the ignited fuel and air are directed in a direction generally towards one of the tube such that a partial vacuum condition is created after the gases and a thrust from the mass flow of the gases is created in the opposite direction of the gas flow to cause a pumping or propelling action.

Description

United States Patent 1 1 3,685,294 Nelson [45] Aug. 22, 1972 HOT GAS PUMPS AND THRUSTERS 3,525,474 8/1970 Von Ohain et al. ..60/264 [72] Inventor: Daniel E. Nelson, 2 David Ave.y 2,938,658 5/1960 1 05161 ..60/264 Apt Na 13, Pacific GroV Calm 3,169,368 2/1965 Munding ..60/264 93950 3,001,691 9/1961 Salmon 6113.1. ..60/264 Filedl y 1970 Primary ExaminerCarlton R. Croyle [21] No; 34 257 Assistant Examiner-Warren Olsen 2 [57] ABSTRACT g1} 8|. ..60/266,60/39.3Fld26l)/72g3 This is a hot g drcdger or p p in which com [58] Fieid 221 222 pressed air is mixed with fuel and ignited in a com- 6 bustor near the end of a tube into which hot gases from the ignited fuel and air are directed in a direction generally towards one of the tube such that a partial [56] References cued vacuum condition is created after the gases and a UNITED STATES PATENTS thrust from the mass flow of the gases is created in the l 305 340 6/1919 Best do 6 opposite direction of the gas flow to cause a pumping 6 t 2,977,753 4/1961 Bailet ..60/266 or pmpe mg ac 2,828,608 4/1958 Conlin et al. ..60/39.32 4 Claims, 2 Drawing Figures HOT GAS PUMPS AND THRUSTERS Pumps or dredges using compressed air directed into a tube have been used previously. Some have been constructed to cause the compressed gas or air to flow axially with the direction of the tube. Others have caused the gas to or air to enter tangentially to cause a cyclone effect In order to increase the momentum of mass travel within the tube.

It is the purpose of this invention to provide hot combustion gases in place of compressed air only into the submerged end of a tube-type dredge or thruster.

It is a further purpose of this invention to provide hot gas propellent for a pump with either cyclone or noncyclone effect.

It is a further purpose of this invention to provide a reactionary engine with an air augmentation channel or inlet through the center of the engine and employing this pumping or propelling device as the nozzle and air augmentation or bypass inlet.

It is a further purpose of this invention to provide a regenerative combustion cycle as an option to aid in fuel economy by eliminating the substantial portion of fuel that would otherwise be required for heating the intake air to effective combustion heat after ignition is accomplished.

This invention is illustrated in the accompanying drawings as follows:

FIG. 1 is a side view cut-away.

FIG. 2 is a top view cut-away. I

The operation of these improvements in gas dredges and pumps is accomplished in the following manner.

Compressed air or other gas is pumped to pump tube 1 through intake tube 2. The compressed air or other gas is directed into an intake housing 3 and then through combustor 4 in regenerative tubes 5. Flame or combustion heat in the combustor causes the compressed air to be at a high temperature from passage through the regenerative tubes in the combustor. When the heated gas reaches the opposite end of the regenerative tubes, it accumulates in a regenerative manifold 6. In the regenerative manifold, the heated gas is directed around the outside periphery of the combustor and then into the combustor through combustor inlet ports 7. Fuel injectors 8 are positioned at several positions, prefferably four, around the periphery of the combustor with injector orifices terminating inside of the combustor. An igniter 10 is positioned near one of the injectors inside the combustor to provide initial heat for ignition. Exhaust orifices 1 l are provided in the wall of the pump tube.

One option within the intent of this. invention is to construct the orifices in a tangential pattern or in a nontangential pattern with the angle of entry in an axially direction only with respect to the pump tube rather than tangentially to the tube wall also.

Another option within the intent and claims of this invention is to eliminate the regenerative cycle of combustion and ignite the compressed air or gas without be regeneratively pre-heated. This is accomplished by omitting two items shown in the drawing and not otherwise changing the device except for filling in the vacancies with material where the parts would otherwise be. The two parts to eliminate are the regenerative tubes 5 and the regenerative wall 12. When the regenerative wall is eliminated and there are no tubes, and no entry thereat into the combustor, the compressed gas will flow around the periphery of the combustor and be directed into the combustor inlet ports 7 without being preheated and will be ignited in the same manner as when the regenerative cycle is employed though the fuel economy will not be as advantageous.

Insulation 13 can be added around the outside periphery of the regenerative manifold to prevent heat loss. This is advantageous with either the regenerative or the non-regenerative combustion cycle.

In using this invention for a thruster, the intake air would be directed into the regenerative manifold from the opposite end thereof, though this is not necessarily the case.

Several compressors have been devised by the applicant for use with this device for either pumping or propelling. Some are turbine. Others are non-turbine. All are very light and efficient in comparison to conventional turbine systems. More significantly, however, neither of them require power take off from the exhaust gases. The compressor can belocated separately from the thrust generating portion of the engine that is described and claimed in this patent application. Streamlining also is not necessary as it is intended that thruster or thrust chamber be positioned within a fuselage for most applications. Thus there is very little difference other than the material of construction that is required for a dredge pump in water, an ocean mining device or a jet engine thrust chamber. Hence, both are included in this specification and the appended claims.

Whether one fuel injector or several are used, it is advisable to have the injector orifices at right angles with the injector or wherever positioned, fuel streams therefrom should be axial to the tube and at several parallel angles.

What is claimed is:

l. A hot gas pump or thruster having a pump tube open at both ends,

a combuster positioned around the outside periphery of the pump tube,

a housing positioned at a distance around the outside periphery of the combustor,

a compressed inlet air means in communication with the inside periphery of the housing,

combustion inlet ports in communication between the inside and the outside periphery of the combustor,

exhaust orifices in communication between the combustor and the inside periphery of the pump tube in an axially angled pattern with respect to the pump tube,

a fuel injection means in communication with the inside periphery of the combustor, and

a means of igniting fuel within the combustor.

2. In a hot gas pump or thruster as described in claim exhaust orifices in an axially angled pattern with respect to the periphery of the pump tube circumference.

3. In a hot gas pump or thruster as described in claim an intake housing in communication with the compressed inlet air means,

regenerative tubes extended through the combustor and in communication between the intake housing and a position between the combustor and a regenerative manifold, and

a regenerative wall positioned between theintake housing and the regenerative manifold.

4. In a hot gas pump or thruster as described in claim 5 insulation around the outside periphery of a regenerative manifold.

Claims

1. A hot gas pump or thruster having a pump tube open at both ends, a combuster positioned around the outside periphery of the pump tube, a housing positioned at a distance around the outside periphery of the combustor, a compressed inlet air means in communication with the inside periphery of the housing, combustion inlet ports in communication between the inside and the outside periphery of the combustor, exhaust orifices in communication between the combustor and the inside periphery of the pump tube in an axially angled pattern with respect to the pump tube, a fuel injection means in communication with the inside periphery of the combustor, and a means of igniting fuel within the combustor.

2. In a hot gas pump or thruster as described in claim 1, exhaust orifices in an axially angled pattern with respect to the periphery of the pump tube circumference.

3. In a hot gas pump or thruster as described in claim 1, an intake housing in communication with the compressed inlet air means, regenerative tubes extended through the combustor and in communication between the intake housing and a position between the combustor and a regenerative manifold, and a regenerative wall positioned between the intake housing and the regenerative manifold.

4. In a hot gas pump or thruster as described in claim 1, insulation around the outside periphery of a regenerative manifold.