DE1089218B - Device for switching on and off combustion chambers, especially for gas turbines and jet engines - Google Patents

Description

The main patent 1 008 963 relates to a device for igniting and re-igniting combustion chambers, especially for gas turbines and jet engines, with a gasification chamber into which a permeable Material existing and pressurized with fuel, closed on one side Pipe protrudes and into which an oxygen carrier is introduced tangentially, which is the outer wall swirls around the pipe and is mixed with the fuel that has seeped through the pipe wall mixes, whereby the mixture jet is ignited and enters the combustion chamber to be ignited.

The invention is a further development of the device according to the main patent and aims, in particular proper ignition or re-ignition of the combustion chamber of a gas turbine or jet engine of aircraft flying at high altitude and at high speed, d. H. also under the most unfavorable ignition conditions with certainty.

According to the invention, a jet pump is provided in a device according to the main patent, which is acted upon by the mixture jet emerging from the gasification chamber as propellant gas and oxygen sucks.

The oxygen intake pipes preferably open into the Jet pump tangentially into the jet pump housing, so that it is the oxygen from its mixture give a vortex movement with the mixture jet. • According to a further feature of the invention can as the oxygen carrier in the gasification chamber, oxygen can be used, and a hypergolic fuel, such as. B. hydrogen phosphide, Hydrogen silicide, zinc methyl, zinc ethyl, phosphine or cacodyl, can be used.,, ;;

In a special embodiment of the device according to the main patent, the mixture is. beam before it enters the combustion chamber to be ignited. chamber ignited by an ignition element, and around at Such an embodiment provides increased security for proper ignition and re-ignition To create the combustion chamber at high altitude and at high flight speeds is according to one Another feature of the invention is the ignition element as an electrically heated rod made of refractory material formed and arranged in the vicinity of the outlet opening of the gasification chamber.

The two power supply lines to the ignition rod are preferably isolated from the gasification chamber, " and in an expedient embodiment the ignition rod is bent in a U-shape.

The invention is illustrated below with reference to the drawing tion explained in more detail, for example. , · Fig. 1 is a schematic axial section through Device for ignition

and reignition of combustion chambers, particularly for gas turbines

and jet engines

Addendum to patent 1 008 963

Applicant:

Societe Nationale d'Etude

et de Construction de Moteurs

d'Aviation, Paris

Representative: Dr. E. Wiegand, Munich 15,

and Dipl.-Ing. W. Niemann, HambuTg 1, Ballindamm 26,

Patent attorneys

Claimed priority: France, February 3, 1958

Raymond Pierre Alfred Lamouche, Paris, and

Jean-Marie Hardy, Esbly, Seine-et-Marne (France)

have been named as inventors

the combustion chamber of a jet engine with a device according to the invention with electrically heated Ignition device;

Fig. 2 is an enlarged side view of the gasification chamber and the ignition member of the device;

Fig. 3 is an axial section through an embodiment of a device according to the invention with jet pump;

Fig. 4 shows in section a modification of the means for introducing and heating an oxygen carrier into the gasification chamber;

Fig. 5 shows in section another embodiment of the device according to the invention,

FIG. 6 shows a partial section along the line VI-VI of FIG. 5;

Fig. 7 shows in section a further embodiment of the invention.

'In Fig. 1, 1 denotes the combustion chamber of a jet engine of an aircraft. the

009 607/116

Combustion chamber has a main fuel injector 2 and a burner 20 surrounding the injector, which is in communication with the air inlet duct 3 of the jet engine. The passage of air between the The wall of the combustion chamber 1 and the outer wall 16 of the engine are of a tubular part 13 passes through, which opens into the combustion chamber 1 and which the device for ignition and re-ignition the combustion chamber receives.

This device has a gasification chamber 8, which via lines 4 with a not shown Source of an oxygen carrier is connected. In the Sections of the lines 4 adjoining the gasification chamber 8 are made of refractory insulating material cylindrical body 6 arranged, and an electrical heating resistor 7 is either around the Body 6 (Fig. 3) or in the bodies 6 (Fig. 4). The flowing through or over the body 6, z. B. heated to about 200 ° C oxygen carrier enters the gasification chamber 8 tangentially through openings 9 so that it is in the gasification chamber a whirling motion is imparted.

A tube 11, closed on one side and made of permeable material, protrudes into the gasification chamber 8, which is acted upon from a line 12 with fuel under pressure, which is passed through the wall of the Tube 11 seeps through and is distributed over its outer surface. The leaked fuel is generated by the heated oxygen carrier swirling around the pipe 11 within the gasification chamber 8 quickly gassed. The resulting gas mixture ignites by itself and leaves the gasification chamber 8 through the outlet opening 10 in the form of a jet which enters the combustion chamber 1 to be ignited penetrates deeply.

The jet emerging from the gasification chamber 8 acts on a jet pump (Fig. 3), which formed by a jet pump housing 22 surrounding the outlet opening 10 of the gasification chamber 8 is, in which pipes 23 connected to an oxygen source open tangentially, so that the Oxygen sucked in by the jet pump causes a vortex movement in the space 21 of the pump housing 22 is issued before it comes to the exiting from the gasification chamber 8, acting as a propellant gas Beam mixes.

If compressed air is supplied to the gasification chamber 8 as an oxygen carrier, it is expedient an electrical ignition element is used to ignite the mixture jet.

In the case of the. Fig. 1 and 2 reproduced embodiment, the electrical ignition member has the form one made of refractory material, such as. B, silicon: carbide or a chromium-nickel alloy, existing U-shaped resistance rod 17, the bent part of which is close to but outside the outlet opening 10 of the gasification chamber 8 is arranged and an electrical voltage is applied to its legs 18 can be to heat the bent part of the resistance rod 17 to a temperature. Of the The U-shaped rod 17 is isolated from the gasification chamber 8 by its legs 18, as can be seen from FIG. 2, are passed through an insulating sleeve 19 between the inner surface of the tubular Part 13 and the cylindrical outer surface of the gasification chamber 8 is arranged. The staff 17 can therefore be easily expanded to make it z. B. against another rod with a different resistance value to adapt the device to the. Voltage of an existing on board the aircraft Replace the voltage source. Furthermore, by the arrangement shown in FIG U-shaped rod 17 the distance of its curved part from the outlet opening of the gasification chamber 8 can be easily adjusted.

Ignition by an electrical resistor has the advantage that a high voltage source is avoided and that immediately a current supplied by the accumulator battery located on board can be used. The supply of the current to the insulated legs 18 of the U-shaped resistance rod 18 avoids the disadvantages of ionizing the surrounding air at high altitudes.

In all cases, a jet flame is used with a large Penetration, which causes a quick and safe ignition of the combustion chamber. The gassing chamber 8 is expediently arranged so that the pilot flame is directed into the zones of the combustion chamber which are most favorable for ignition, e.g. B. in the zones behind the screens of the main injector 2 surrounding burner 20.

The oxygen supply and the heating of the resistors 7 and the rod 17 of course only need in to be put into operation the moment the combustion chamber is ignited or reignited shall be.

In the embodiment according to FIGS. 5 and 6, an ignition rod 24 is inside the gasification chamber 8 placed near their outlet opening, which allows the use of straight rods of small dimensions and simple form. The ignition rod 24 shown in Figs. S and 6 is a cylinder made of silicon carbide. Two inserts through insulating material 26 passed through conductors 25 provide the mechanical Holders and electrical power supplies for the ignition rod 24.

In the modified embodiment shown in FIG. 7, the permeable pipe 11 is _{fed from the line 12 with a hypergolic fuel such as liquid hydrogen phosphide P 2} H ₄ , liquid hydrogen _{silicide Si 2} H ₆ , zinc methyl, zinc ethyl, phosphine or cacodyl. Such fuels are spontaneously ignited by sudden oxidation on contact with the oxygen carrier (pure oxygen or in certain cases compressed air) which is fed to the gasification chamber 8 through the tangential lines 4. The ignition element 17 or 24 and the heating resistors 7 can then be omitted.

Claims (7)

Patent claims: 1. Device for igniting and re-igniting combustion chambers, in particular for gas turbines and jet engines, with a gasification chamber in which a material made of permeable material and a pipe which is closed on one side and pressurized with fuel protrudes into it and introduced into the tangential an oxygen carrier is, which flows around the outer wall of the tube and swirls with the through the Mixes fuel leaked through the pipe wall, the mixture jet being ignited and into the combustion chamber to be ignited enters, according to patent 1 008 963, characterized by a jet pump (21, 22/23), which is acted upon by the mixed jet as propellant gas and draws in oxygen. 2. Device according to claim 1, characterized in that the oxygen intake pipes (23) tangentially into the jet pump housing (22) ι o «y open and give the oxygen a vortex movement before mixing with the mixture jet. 3. Apparatus according to claim 1 and 2, characterized in that oxygen is used as the oxygen carrier. 4. Apparatus according to claim 1 to 3, characterized in that a hypergolic fuel, such as z. B. hydrogen phosphide, hydrogen silicide, zinc methyl, zinc ethyl, phosphine or cacodyl are used will. 5. Device for igniting and re-igniting combustion chambers, especially for gas turbines and jet engines, with a gasification chamber in which a material made of permeable material and a pipe which is closed on one side and pressurized with fuel protrudes into it and introduced into the tangential an oxygen carrier is, which flows around the outer wall of the tube and swirls with the through the Mixes fuel that has seeped through the pipe wall, the mixture jet being ignited by an ignition element and enters the combustion chamber to be ignited, according to Patent 1 008 963, characterized in that that the ignition element is designed as an electrically heated rod (17, 24) made of refractory material and is arranged in the vicinity of the outlet opening (10) of the gasification chamber (8). 6. Apparatus according to claim 5, characterized in that the two power supplies are isolated from the gasification chamber to the ignition rod. 7. Apparatus according to claim 5 or 6, characterized in that the ignition rod is U-shaped is bent. 1 sheet of drawings @ | 009 607/116 9.60