RU2002161C1

RU2002161C1 - Liquid fuel burning method

Info

Publication number: RU2002161C1
Authority: RU
Inventors: Сергей Николаевич Пелых; Николай Пантелеевич Бут; Сергей Николаевич Акулов
Original assignee: Сергей Николаевич Пелых
Priority date: 1991-07-08
Filing date: 1991-07-08
Publication date: 1993-10-30

Description

жидкого топлива и центральный поток смеси паров легких фракций жидкого топлива и газообразного окислител . Центральный поток, попада в камеру сгорани , встречаетс с реверсивным потоком продуктов сгорани и воспламен етс , образу приосевую зону устойчивого воспламенени . Периферийный поток, истека из топливного канала 11, распадаетс , обеспечива мелкодисперсный распыл топлива, капли которого попадают в закрученный поток нагретого газообразного окислител , попадающего в камеру сгорани 1 через завихритель 6. В закрученном потоке нагретого газообразного окислител мелкие капли подогретого топлива быстро испар ютс и смешиваютс с окислителем , образу топливную смесь, котора воспламен етс от потока продуктов сгорани приосевой зоны. Продукты сгорани движутс по направлению к сопловому отверстию 2, где разгон ютс и истекают из камеры сгорани . За счет закрутки потока в камере сгорани 1 образуетс приосевой реверсивный поток, который увлекает продукты сгорани навстречу топливной смесиliquid fuel and a central stream of a mixture of vapors of light fractions of liquid fuel and a gaseous oxidant. The central stream entering the combustion chamber meets the reversed flow of combustion products and ignites, forming the axial zone of stable ignition. The peripheral stream flowing out from the fuel channel 11 disintegrates, providing a finely dispersed fuel spray, the droplets of which fall into the swirling stream of heated gaseous oxidizer entering the combustion chamber 1 through swirl 6. In the swirling flow of heated gaseous oxidizer, small droplets of heated fuel quickly evaporate and mix with an oxidizing agent, forming a fuel mixture that ignites from the flow of combustion products of the axial zone. The combustion products move towards the nozzle opening 2, where they accelerate and flow out of the combustion chamber. Due to the swirling of the flow in the combustion chamber 1, an axial reverse flow is formed, which entrains the combustion products towards the fuel mixture

Claims

The claims

METHOD FOR LIQUID FUEL COMBUSTION, including preliminary heating of a gaseous oxidizer, its supply and liquid fuel to a combustion chamber.

PRI me R. Air is supplied to the combustion chamber at a pressure of 0.5-0.7 MPa. Air flow rate is 50-60 g / s. Diesel fuel with a flow rate of 3-4 g / s is supplied to the fuel channel

5 The internal diameter of the combustion chamber is 32 mm, the diameter of the critical section of the nozzle of the combustion chamber is 11.5 mm, and the internal diameter of the fuel channel is 14 mm. The ratio of the area of the holes in the wall of the fuel

10 channels and passages in the air swirl 0.24, the Combustion of fuel will be 0.91-0.96.

Technical appraisal and economic advantages 15 of the claimed method in comparison with the prototype method consist in increasing the completeness of fuel combustion from 0.75-0.85 (for the prototype) to 0.91-0.96 (for the claimed method) due to the improvement quality of preparation of the fuel mixture

(56) 1. USSR author's certificate N 1465525. cl. E 21 B 7/14, 1989.

2. Copyright certificate of the USSR 25 Ms 209369, cl E 21 C 37/16, 1968.

characterized in that the liquid fuel stream is fed into the combustion chamber in the form of a rotating cylindrical layer, and 30 a gaseous oxidizer is introduced into the fuel stream perpendicular to the generatrix of the cylindrical layer