CN211819659U

CN211819659U - Liquid oxygen combustion-supporting engine

Info

Publication number: CN211819659U
Application number: CN202020072963.3U
Authority: CN
Inventors: 宋尧
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-01-14
Filing date: 2020-01-14
Publication date: 2020-10-30
Anticipated expiration: 2030-01-14

Abstract

A liquid oxygen combustion-supporting engine comprises a turbine type aero-engine and an oil gas inlet pipe of a combustion chamber of the turbo type aero-engine, wherein a sleeve is sleeved on the periphery of the oil gas inlet pipe, a plug is installed at one end of the sleeve in the combustion chamber, an oxygen gas injection hole is formed in the plug, and a gap is formed between an inner ring of the plug and the periphery of the oil gas inlet pipe; the sleeve outside the combustion chamber is hermetically connected with the oil gas inlet pipe; the sleeve is communicated with a gasifier, and the gasifier is communicated with a liquid oxygen pipeline. The utility model adds a pure oxygen inlet at the inlet of the existing oil gas pipeline into the combustion chamber, so that the power-assisted oil gas can be fully combusted, and the driving force is increased; improve combustion efficiency and save cost.

Description

Liquid oxygen combustion-supporting engine

Technical Field

The utility model relates to the technical field of engines, concretely relates to combustion-supporting engine of liquid oxygen.

Background

The fuel combustion efficiency of the turbine aeroengine is usually 22-36 liters/100 tons kilometers, and the fuel consumption of the piston engine of the diesel-oil-burning automobile is usually 45L/100 kilometers; the root cause of the large gap is the severe shortage of oxygen supply. Combustion theoretical oxygen/fuel volume ratio of about 2: 1; therefore, pure liquid oxygen is introduced into the combustion chamber of the engine to support combustion, and the air intake is reduced, so that the energy clean use technology is provided.

SUMMERY OF THE UTILITY MODEL

The utility model provides a combustion-supporting engine of liquid oxygen improves combustion efficiency, practices thrift the cost.

The utility model discloses the technical scheme who adopts does:

a liquid oxygen combustion-supporting engine comprises a turbine type aero-engine and an oil gas inlet pipe of a combustion chamber of the turbo type aero-engine, wherein a sleeve is sleeved on the periphery of the oil gas inlet pipe, a plug is installed at one end of the sleeve in the combustion chamber, an oxygen gas injection hole is formed in the plug, and a gap is formed between an inner ring of the plug and the periphery of the oil gas inlet pipe; the sleeve outside the combustion chamber is hermetically connected with the oil gas inlet pipe; the sleeve is communicated with a gasifier, and the gasifier is communicated with a liquid oxygen pipeline.

A gas oxygen inlet pipe is connected into the combustion chamber, the gas oxygen inlet pipe is communicated with a gasifier, and the gasifier is communicated with a liquid oxygen pipeline.

The plug is coated with a ceramic layer containing rhenium rare earth.

The liquid oxygen combustion-supporting engine comprises a piston type engine and an oil/air mixed gas or fuel oil inlet pipe, wherein an oxygen inlet pipe is additionally arranged in the oil/air mixed gas or fuel oil inlet pipe.

The utility model adds a pure oxygen inlet at the inlet of the existing oil gas pipeline into the combustion chamber, so that the power-assisted oil gas can be fully combusted, and the driving force is increased; improve combustion efficiency and save cost.

The utility model can also be used for turbojet engines, turboprop engines, turbine shaft engines, paddle fan engines, piston aircraft engines and automobile piston engines; the invention can also be used in detonation engines and gas turbines for deep space aircraft.

Drawings

Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention;

fig. 2 is a schematic plan view of the plug of the present invention;

fig. 3 is a schematic structural diagram of embodiment 2 of the present invention.

Detailed Description

The present invention and the effects thereof will be further explained with reference to the accompanying drawings.

Embodiment 1, referring to fig. 1 and 2, a certain type of turbo turbofan engine 1 is taken as an example, and includes an air inlet 2; a compressor 3; a combustion chamber 4; a turbine 5; a nozzle 6, an engine tail 7; the conventional oil gas inlet pipe 8 and the afterburner nozzle comprise a conventional oil gas or pure fuel oil inlet 15.

The liquid oxygen combustion-supporting engine comprises a turbine type aero-engine and an oil gas inlet pipe 8 of a combustion chamber of the turbo type aero-engine, wherein a sleeve 9 is sleeved on the periphery of the oil gas inlet pipe 8, a plug 13 is installed at one end of the sleeve 9 in the combustion chamber 4, an oxygen spraying hole 14 is formed in the plug 13, and the number of the oxygen spraying holes 14 is 2-6. A gap 12 is arranged between the inner ring of the plug 13 and the periphery of the oil gas inlet pipe 8; the oxygen ejection holes 14 and the gaps 12 are provided to uniformly eject oxygen to prevent coking and clogging of the inner tube nozzle. A sleeve 9 outside the combustion chamber 4 is hermetically connected with an oil gas inlet pipe 8; the sleeve 9 is communicated with a gasifier 10, the gasifier 10 is communicated with a liquid oxygen pipeline 11, the liquid oxygen pipeline 11 is communicated with a liquid oxygen storage tank, and the liquid oxygen storage tank is installed at the crude oil fuel storage tank, except that the volume of the crude oil fuel storage tank is reduced. The gasifier 10 is made of OR oxidation resistant alloy steel pipe, and the pressure resistance in the pipe is more than 15 Mpa.

A gas oxygen inlet pipe 16 is connected into the combustion chamber 4 for assisting combustion.

The plug 13 is coated with a ceramic layer containing rhenium-based rare earth. Can resist high temperature of more than 3000 ℃.

After the structure is applied to the turbine turbofan type aircraft engine, the main power indexes are as follows: the fuel efficiency is less than 21L/100 ton kilometer, the oxygen-fuel-gas ratio is more than 1.2 (V/V), and the raw fuel-gas ratio is less than 0.8.

Embodiment 2, referring to fig. 3, a piston engine of a certain type is exemplified, and comprises a cylinder 21, a crankshaft connecting rod 22, a piston 23, an oil-gas preheater 25, an oil/air mixture or fuel oil inlet 26, a mixture inlet valve 27, an electronic igniter 28, an exhaust gas discharge valve 29, and an exhaust gas discharge port 20.

A liquid oxygen combustion-supporting engine comprises a piston engine and an oil/air mixed gas or fuel oil inlet pipe 26, wherein an oxygen inlet pipe 24 is additionally arranged in the oil/air mixed gas or fuel oil inlet pipe 26. It is made of OR oxidation resistant alloy steel pipe with pressure resistance higher than 15 MPa.

After the structure of the embodiment 2 is applied to the piston engine, the main power indexes are as follows: the oil consumption is less than 41L/100 kilometers, and the fuel-gas ratio is more than 1.1 (V/V).

The beneficial effects of the present invention will be further explained by the following specific application examples.

1. The existing fuel system of a turbofan engine with a certain model is improved into an on-duty combustion nozzle according to the utility model; taking kerosene with the molecular weight of 198 and the specific gravity of 0.7; the liquid industrial oxygen storage tank is designed and configured with the oxygen molecular weight of 32 and the liquid oxygen density of 1.141g/cm3(-182.96 ℃, 10.1 Mpa); the material is selected from T700 carbon fiber coated with 400-mesh heat preservation micro-beads, and fused engineering plastics mechanically wrapped with a metal interlayer to be made into a cylinder shape; the pressure resistance of the storage tank is more than 15 Mpa.

Use the utility model discloses the back, change into at the appointed berth of airport loading aviation kerosene 10M3 and liquid industry oxygen 10M3 with the aviation kerosene fuel carrying capacity 20 tons of a certain model standard, can satisfy normal flight demand. When the airplane takes off, the computer program control system commands the engine to normally ignite, then gradually reduces the air inlet quantity and increases the oxygen quantity to reach the specified thrust. After the utility model is used, the diameter of the air compressing turbofan of the engine can be reduced by more than 10 percent, and the fuel efficiency can reach below 20 liters/100 ton kilometers; an increase in fuel efficiency of > 10% is also equivalent to an increase in the cruising range of the aircraft.

2. A certain model 100-ton load series chemical tower carrying traction automobile is provided with a liquid oxygen supply system of the existing piston engine; meanwhile, an original square fuel tank is modified, and a 1.0M3 fuel tank is divided into a diesel oil 0.5M3 and a liquid industrial oxygen 0.5M3 cylindrical fuel tank. Use the utility model discloses afterwards, it is combustion-supporting to add liquid oxygen for carrying the car substep when refueling, has improved combustion efficiency, and automobile engine oil consumption reduces to < 40L 100 kilometers.

Claims

1. A liquid oxygen combustion-supporting engine comprises a turbine type aero-engine and an oil gas inlet pipe (8) of a combustion chamber of the turbine type aero-engine, and is characterized in that a sleeve (9) is sleeved on the periphery of the oil gas inlet pipe (8), a plug (13) is installed at one end of the sleeve (9) in the combustion chamber (4), an oxygen spraying hole (14) is formed in the plug (13), and a gap (12) is reserved between an inner ring of the plug (13) and the periphery of the oil gas inlet pipe (8); a sleeve (9) outside the combustion chamber (4) is hermetically connected with an oil gas inlet pipe (8); the sleeve (9) is communicated with a gasifier (10), and the gasifier (10) is communicated with a liquid oxygen pipeline (11).

2. A liquid oxygen combustion engine according to claim 1, characterized in that a gas oxygen inlet pipe (16) is connected to the combustion chamber (4), and the gas oxygen inlet pipe (16) is communicated with the gasifier (10).

3. A liquid oxygen combustion engine according to claim 1, characterized in that the bulkhead (13) is coated with a ceramic layer containing rhenium based rare earth.