SU1712640A1 - Exhaust manifold of internal-combustion engine - Google Patents

Abstract

The invention relates to mechanical engineering, in particular, to engine-building, and allows for improving the fuel economy of an engine by eliminating exhaust gas from the exhaust manifold into the engine cylinders. The exhaust manifold contains channels 1 and 2, each of which is connected to a group of cylinders 3, 4 and provided with a pressure stabilizer 5, 6 in the outlet part, containing a nozzle 7, 8 narrowed in the direction of the outlet from the collector and an annular vortex between the nozzle and the outlet of the collector chamber 9, 10, stabilizer nozzles are connected by an additional channel 13, while the points of intersection of the axes of the nozzles and the additional channel are located in the narrowed areas of the nozzles. To improve the processability of the design, the additional channel 13 is perpendicular to the axes of the nozzles connected by it, the narrowed part of which is made in the form of cylinders 11 and 12. 1 Cp f-ly, 2 il.sls

Description

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The invention relates to mechanical engineering and can be used in internal combustion engines.

The aim of the invention is to increase the fuel economy of the engine by improving the filling of the cylinders with fresh charge by smoothing the reflected pressure waves in the exhaust ducts.

FIG. 1 shows the collector, section, general view; in fig. 2 - pressure stabilizers, cut.

The manifold contains at least two channels 1 and 2 connecting the exhaust pipes 3 and 4 of the cylinders with non-overlapping exhaust phases (due to the alternation of operating cycles in the engine cylinders).

In each collector channel, in its outlet part, pressure stabilizers 5 and 6 are installed, including nozzles 7 and 8, respectively, tapered towards the exit of the collector and enclosed vortex chamber 9 and 10 between the nozzles and the collector outlets of the Bbie ring have narrowed portions 11 and 12. The narrowed portions of the pressure stabilizers are connected by an additional channel 13, the axis of which is perpendicular to the axis of the nozzles connected by it and crosses the latter in their narrowed portions.

The exhaust manifold works as follows.

Due to the fact that channels 1 and 2 unite groups of cylinders with non-overlapping exhaust phases, while in channel 1 the exhaust from the cylinder ends and the gas pressure is close to the minimum, in channel 2 the pressure is close to the maximum and vice versa during the maximum pressure Channel 1 shows a minimum of pressure in the second channel, i.e. processes in channels 1 and 2 are in antiphase.

At the beginning of the release from the cylinder attached to it — in channel 1 the pressure is intensely increasing, the exhaust gases from channel 1 enter the nozzle 7 of the pressure stabilizer 5, where their pressure decreases and the speed increases, and expire at a high speed through the constricted part 11 of the nozzle, the annular vortex chamber 9 and further in the gas inlet of the turbine, or a silencer (not shown). At the same time, part of the gases from the narrowed part 11 of the stabilizer nozzle 5 flows through the channel 13 into the narrowed part 11 of the stabilizer nozzle b of the pressure of the adjacent channel 2, where at this time the pressure is less than in the channel. In the final phase

The release pressure in channel 1 decreases and a reverse pressure wave occurs, causing the exhaust gases to move in the opposite direction.

When interacting backflow

with the walls of the annular vortex chamber 9, a toroidal vortex is formed, compressing the reverse flow into a narrow submerged jet, directed along the axis of the constricted

parts of the stabilizer nozzle 5.

At this time, the first phase of the exhaust from the next cylinder flows in channel 2, the pressure in the constrictor nozzle 12 is 6 more than in the constrictor nozzle 11

stabilizer nozzles 5 and through the channel 13 part of the exhaust gas enters the stabilizer 5. Since the channel 13 is directed perpendicular to the axis of the stabilizer 5, the flow from the channel 13 turbulent reverse jet

gases in the narrowed part of the stabilizer nozzle 5 and squeezes it from the axis to the wall of the nozzle 7. Due to the asymmetry of the flow at the outlet of the nozzle 7 in front of him there is a macrovortex. So in the final part

release in the stabilizer 5 pressure there are three zones of energy dissociation; a toroidal vortex in a ring-shaped vortex chamber 9, a microturbulence zone in the narrowed part 11 of the nozzle and a macrovortex at the exit

from the nozzle, which effectively smooths the reflected pressure waves in the exhaust manifold. Gas-dynamic processes in the channel 2 of the collector and the stabilizer 6 pressure proceed similarly

indicated.

Claims (2)

1. An exhaust manifold for an internal combustion engine containing at least at least one pair of channels, each of which is connected to a group of cylinders with non-overlapping exhaust phases and equipped in the outlet part with a pressure stabilizer made in the form of a narrowed an annular vortex chamber, which, in order to increase the fuel efficiency of the engine, the nozzles of each pair of pressure stabilizers are connected an additional channel, with the intersection points of the axes of the nozzles and the additional channel located in the constricted areas of the nozzles. 2. Collector pop. 1, characterized in that the additional channel is perpendicular to the axes of the nozzles connected by it, the constricted part of which is made in the form of a cylinder.