# US 6,295,802 B1 · Orbiting engine

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- Number: US 6,295,802 B1
- Document ID: US6295802B1
- Status: Granted
- Kind: B1
- Application number: 09/269,638
- Filed: 1999-03-31
- Granted: 2001-10-02
- Earliest claimed: 1996-10-01
- Assignees: David Lior
- Inventors: David Lior; Yeshayahu Levy
- Web page: https://patentgrep.com/patent/US6295802B1

## CPC

- F02C 3/165: {the combustion chamber contributes to the driving force by creating reactive thrust}
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)

## Abstract

An orbiting engine includes a plurality of combustion chambers (52) rigidly connected to and disposed equidistantly from a central shaft (54). The combustion chambers (52) are oriented so that exhaust gases emerge therefrom tangentially to a circle concentric with the shaft (54), thereby causing the shaft to rotate. In preferred embodiments, a centrifugal compressor (62), radially inward from the combustion chambers (52) and driven by the shaft (54), compresses air that serves to oxidize fuel injected into the combustion chambers (52).

## Claims

### Claim 1

An engine for driving a load shaft, comprising:
(a) a power shaft; and
(b) a plurality of combustion chambers, each of said chambers being substantially equidistant from said power shaft and rigidly connected to said power shaft, each of said chambers being provided with a nozzle oriented so that exhaust gases exit said chamber therethrough in a direction substantially tangential to a circle concentric with said power shaft;
(c) an oxidizer supply mechanism for supplying oxidizer laterally to said chambers, said oxidizer supply mechanism including:
(i) a compressor rotor, substantially coaxial with said power shaft;
(ii) a diffuser, substantially coaxial with said power shaft and deployed between said compressor and said chambers; and
(iii) a plurality of vanes, peripheral to said diffuser, wherethrough compressed air is introduced to said chambers; and
(d) a fuel supply mechanism for supplying fuel to said chambers.

### Claim 2 (depends on 1)

The engine of claim 1, wherein said rigid connection of said chambers to said shaft is provided by a disc substantially coaxial with said power shaft.

### Claim 3 (depends on 1)

The engine of claim 1, wherein said fuel supply mechanism includes a fuel injector in each of said chambers.

### Claim 4 (depends on 1)

The engine of claim 1, further comprising a transmission mechanism for transferring power from said power shaft to the load shaft and to said compressor.

### Claim 5 (depends on 4)

The engine of claim 4, wherein said transmission mechanism includes a differential planetary transmission.