RU2791175C1 - Gas turbine engine combustion chamber - Google Patents

Abstract

FIELD: aircraft engine construction.

SUBSTANCE: invention relates to aircraft engine construction, in particular to gas turbine engines with combustion chambers with radial fuel supply via a sawing disc on the rotor shaft. A gas turbine engine annular combustion chamber contains a casing, a flame tube with a number of apertures for supplying air in the combustion zone and a mixing zone for reducing gas temperature before the turbine atomizing disk on the fuel supply rotor shaft, an ignition plug, an annular collector connected via a pipe to the connector of additional air in an atomizing disk cavity is installed in the basis of a flame tube.

EFFECT: invention provides possibility to reduce engine starting time by means of quality fuel atomizing and mixing with additional air (or oxygen) in the ignition zones, and stabilizing fuel-air mixture combustion during engine starting.

1 cl, 1 dwg

Description

The invention relates to the field of aircraft engine building, in particular, to gas turbine engines with combustion chambers with radial fuel supply through a spray disc on the rotor shaft.

The processes of mixture formation in the combustion chambers of gas turbine engines significantly affect the start-up process, the organization of combustion, the reliability and efficiency of the combustion chambers, the temperature regime of individual elements of the hot part of the engines.

A well-known design of the annular combustion chamber of a gas turbine engine with a radial supply of fuel through a spray disk on the rotor shaft, including a housing, a flame tube with rows of holes for supplying air to the combustion zone, holes for reducing the gas temperature in front of the turbine and an electric spark plug located on the combustion chamber housing [1]. To increase altitude and improve launch, oxygen is supplied to the candle [2].

The disadvantage of the described annular combustion chamber of a gas turbine engine with a radial fuel supply is the starting process, while an electric candle mounted on the body ignites the air-fuel mixture, which at the initial stage, when oxygen is supplied, burns only in the area of the candles and freely exits through the turbine nozzle apparatus. As the combustion products warm up, the flame front from the candles expands and descends to the atomizing disk on the rotor shaft and stably stabilizes in the zone of vortices formed behind the transverse air jets from the air supply holes closest to the shaft into the flame tube. However, at negative temperatures and reduced air pressure at the engine inlet, the start-up time and stable combustion stabilization increase and do not fit into the specified norms.

The objective and technical result of the invention is to reduce the engine start time by creating high-quality fuel atomization and mixing with additional air (or oxygen) at the exit from the atomizing disk to the combustion stabilization zone.

The problem is solved by the fact that at the base of the flame tube there is an annular bushing with a manifold for supplying fuel to the atomizing disk, which has channels for supplying additional air (or oxygen) from a separate pipeline with a fitting into the cavity of the atomizing disk to create an air differential on its injector holes and improve atomization of fuel in the flame stabilization zone at the transverse air supply holes closest to the shaft in the flame tube.

The essence of the invention is illustrated by the drawing of the combustion chamber of a gas turbine engine (Fig. 1), where

1 - housing of the combustion chamber;

2 - outer shell of the flame tube;

3 - spark plug;

4 - fuel supply manifold;

5 - spray disc;

6 - holes for stabilizing the flame behind the air jets;

7 - inner shell of the flame tube;

8 - annular sleeve for supplying fuel and additional air (or oxygen).

9 - fitting for supplying additional air (or oxygen);

10 - pipeline;

11 - holes for air supply to the base of the flame tube;

12 - flame stabilization zone.

The combustion chamber includes a housing 1, an outer shell 2 of the flame tube, a spark plug 3, a fuel supply manifold 4, a spray disc 5 on the rotor shaft, holes 6 on the inner shell 7 of the flame tube for stabilizing the flame on air jets, an annular sleeve 8 for supplying fuel and additional air (or oxygen) into the cavity of the spray disc at startup.

Additional air (or oxygen) enters the annular manifold of the bushing 8 through the fitting 9 and the pipeline 10, similar to the fuel line to the manifold 4, and exits into the cavity of the atomizing disc, creating a difference in its nozzle holes, which contributes to high-quality atomization of the fuel and the organization of the fuel-air mixtures. In the outer shell 2 of the flame tube, holes 11 are made for supplying air to the atomizing disk 5. Behind the air jets from the holes 6, a flame stabilization zone 12 is formed in the vortices.

When the engine is started in the combustion chamber housing 1 at the base of the flame tube between shells 2 and 7, through holes 6 and 11 the main air flow from the compressor is supplied and additional air (or oxygen) is supplied through fitting 9 and pipeline 10 into the annular manifold of bushing 8 in the cavity of the atomizing disc 5 for mixing with fuel, which is also fed through the manifold 4 into the atomizing disc 5. Through the holes in the rotating atomizing disc 5, the fuel is radially scattered and due to the difference of additional air (or oxygen) on its nozzle holes, high-quality atomization and mixing is created fuel with air. With the help of a spark plug 3 installed on the body of the combustion chamber 1, the air-fuel mixture is ignited, which, due to the quality of the atomization of the mixture, propagates into the flame stabilization zone 12 formed behind the jets of the main air flowing transversely through the holes 6 in the lower shell 7 of the flame tube.

Thus, the annular sleeve 8, connected through the pipeline 9 with the fitting 10 for supplying additional air (or oxygen), allows, when starting the engine, to create a high-quality air-fuel mixture in the combustion chamber and the flame stabilization zone at the initial stage of starting, which reduces the time to reach the set mode .

Literature

1. Pchelkin Yu.M. Combustion chambers of gas turbine engines: A textbook for university students studying in the specialty "Turbine Engineering". - 3rd ed. Revised and additional - M.: Mashinostroenie, 1984 - 280 p., ill.

2. Inozemtsev A.A. Fundamentals of designing aircraft engines and power plants: textbook. / A.A. Inozemtsev, M.A. Nikhhamkin, V.L. Sandratsky. - M.: "Engineering", 2008.

Claims (1)

An annular combustion chamber of a gas turbine engine, including a housing, a flame tube with rows of holes for supplying air to the combustion zone and a mixing zone to reduce the gas temperature in front of the turbine, a spray disk on the rotor shaft for supplying fuel, a spark plug, characterized in that at the base of the flame tube an annular collector is installed, connected through a pipeline with a fitting for supplying additional air to the cavity of the atomizing disc.

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