DE1202064B - Combustion chamber for gas turbine engines - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Int. Cl .:

F02c

German class: 46 f- 7/03

Number: 1202064

File number: R 332071 a / 46 f

Filing date: July 26, 1962

Opening day: September 30, 1965

The invention relates to a combustion chamber for gas turbine engines with a disposed therein Fuel injection nozzle and a device through which fuel is supplied to this nozzle, furthermore with a fuel atomizer which extends in the longitudinal direction in the combustion chamber is arranged that substantially all of the fuel exiting the injector on one upstream of the fuel atomizer arranged section is directed, wherein a device it is provided that a stream of combustion air over the fuel atomizer which causes the fuel to travel downstream along the fuel impingement atomizer.

In the formation of such combustion chambers, the task arises, as far as possible, of the fuel to limit the combustion zone and prevent parts of the fuel from being unburned by the Can pass through the combustion chamber.

According to the invention, this object is achieved in an ao combustion chamber of the type mentioned at the beginning solved that the fuel atomizer at its downstream end with deflectors is equipped, which reduce the speed of the fuel passing through and the Deflect fuel in such a way that it runs off the fuel impingement atomizer at right angles to it. This increases the efficiency of the combustion considerably. Since the combustion on a proportionate can be limited to a small axial length, the embodiment according to the invention is suitable especially for engines in which a short overall length of the combustion chamber is desired, because by reducing the velocity of the fuel flowing along the fuel atomizer the possibility is created to distribute the fuel in a favorable manner and to mix it with the primary air to mix in such a way that a suitable fuel-air mixture in a relatively short Mixing space is obtained.

The downstream end of the fuel atomizer is according to a preferred embodiment of the invention on itself to form a channel for the fuel to form the deflector bent back, and the gutter is transverse to the fuel impingement and is opposite on both Ends open. The fuel atomizer is expediently radially inward curved towards the end on the underside of the current. This makes the distribution and mixing in special Dimensions favorably influenced.

In an annular combustion chamber known per se for gas turbine engines

Applicant:

Rolls-Royce Ltd., Derby, Derbyshire

(Great Britain)

Representative:

Dipl.-Ing. C. Wallach, patent attorney,

Munich 2, Kaufingerstr. 8th

Named as inventor:

Denis Richard Carlisle, Risley, Derbyshire

(Great Britain)

Claimed priority:

Great Britain August 3, 1961 (28 322) -

Combustion chamber with several fuel injection nozzles, which are arranged in the circumferential direction at a distance from one another are, according to a further embodiment of the invention in the annular combustion chamber is a annular arrangement of flow guide plates arranged at a distance from one another is provided and the fuel impingement is in the space between each adjacent pair of flow baffles arranged, wherein the guide plates cause the combustion air over the atomizer is still being directed out.

The fuel atomizer itself expediently consists of a plate, which creates a special simple construction results.

Further advantages and details of the invention emerge from the following description of exemplary embodiments on the basis of the drawing. It shows

F i g. Fig. 1 is a partial cross-section through a vertical lift gas turbine engine incorporating an inventive device Combustion chamber,

F i g. 2 and 3 broken cross-sections and the combustion chamber according to FIG. 1 in an enlarged view along the lines H-II in FIG. 3 and HI-III in FIG. 2,

F i g. 4 shows a broken cross section along the line IV-IV in FIG. 2.

A vertical lift gas turbine engine 10 for an aircraft includes an engine housing 11 with a Compressor 12, an annular combustion chamber 13 and a turbine 14.

509 689/109

The annular combustion chamber 13 has an inner wall consisting of two parts 15,15 'which are telescopic are assembled together via a corrugated, annular strip 16. The chamber 13 also has an outer wall consisting of three 5 parts 17, 17 ', 17 "which are also telescopic over intermediate corrugated annular strips 18, 18 'are mounted.

A dilution air line 19 lies between the outer wall 17, 17 ', 17 "and the engine housing 11, while an annular cooling air line 20 between the inner wall 15,15 'and a inner housing 21 is located.

• Part of the air compressed by the compressor 12 flows into the combustion chamber 13 through a primary one or combustion air line 22.

The remaining air compressed by the compressor 12 is sent to the cooling air line 20 and to the dilution air line 19 submitted.

The dilution air flows through the dilution air line 19, is divided in this and entered the combustion chamber 13 by a ring of angularly offset dilution air ducts 23. These Dilution air scoops 23 sit downstream of the combustion zone in the combustion chamber 13, so that the dilution air serves to bring the temperature of the combustion products to a level suitable for the turbine 14 reduce sustainable value.

Part of the air coming from the dilution air line 19 and from the cooling air line 20 flows through between the corrugations of the corrugated ring parts 16, 18, 18 'and forms a cooling film on the walls 15 ', 17', 17 ".

Combustion chambers for gas turbine engines typically use secondary air fed into the combustion chamber is initiated immediately downstream of the combustion zone in order to change the direction of the Support combustion gases and complete the combustion.

No secondary air is used in the combustion chamber 13 and the combustion gases only carry one only change of direction in the combustion zone.

Between the combustion air line 22 and the inner wall 15 there is a ring line 24, which is supplied with fuel via a pipe 25. The ring line 24 supplies fuel to a A plurality of angularly offset injectors 26 each located in the downstream end of the combustion air line 22 extend.

Each fuel injection nozzle 26 operates with a largely rectangular fuel impingement atomizer protruding therefrom 27 together. Essentially all of that exiting the injection nozzle 26 beats Fuel on the upstream part of the atomizer plate 27 concerned.

Each fuel atomizer 27, the upstream end of which is on the inner wall of the combustion air duct 22 is attached by a bracket 30, extends lengthwise in the combustion chamber and slopes radially inward downstream. The downstream end of the atomizer plate 27, which is in the Combustion chamber 13 is immediately upstream of the combustion zone, is bent back and forms a gutter 31. This gutter 31 collects fuel flowing downstream along the atomizer plate 27 flows, wherein the channel 31 extends transversely to the plate 27 and is open at both ends 32, 33.

A ring of angularly offset guide plates 34 is located in the combustion chamber 13, wherein a fuel atomizer 27 in each case in the space between two guide plates lying next to one another 34 is provided. Each guide plate 34 is largely rectangular and has side walls 35, 36.

The guide plates 34 direct the combustion air from the combustion air line 22 along the Fuel impingement plates 27 in the form of streams of combustion air which carry the fuel, which flows onto the atomizer plates 27 from the fuel injectors 26, along the plates 27 downstream carries.

Part of the fuel is atomized as soon as it hits the fuel atomizer plates 27, while the remaining fuel collects in the gutters 31 and as it exits the open ends 32, 33 is atomized.

The grooves 31 of the atomizer plates 27 reduce the speed of the fuel flow and cause that the fuel spreads across the plate so that it remains in the combustion zone and does not go through the combustion chamber unburned.

The combustion chamber 13 also has two diametrically opposed additional fuel atomization nozzles 37, only one of which is shown. Each nozzle 37 receives fuel through a pipe 38. An electrical high-voltage igniter 40 sits next to each of these auxiliary nozzles 37 and ignites it atomized fuel.

The additional fuel atomization nozzles 37 and igniters 40 are activated when the engine is started used, but can also be in operation if the main supply of fuel by the Nozzles 26 works.

It can be seen that the fuel baffles 27 are a simple and inexpensive device for atomizing represent of fuel, and that this device is particularly advantageous for vertical lift motors, who only work for a short time.

Claims (6)

Patent claims: 1. Combustion chamber for gas turbine engines with a fuel injection nozzle arranged in it and means through which fuel is supplied to said nozzle, further comprising a Fuel atomizer, which is arranged in the combustion chamber extending in the longitudinal direction is that substantially all of the fuel exiting the injector is in one is directed upstream of the fuel atomizer arranged section, wherein a Means is provided which provides a flow of combustion air over the fuel atomizer which causes the fuel to travel along the fuel atomizer runs downstream, characterized in that the fuel atomizer (27) is equipped at its downstream end with deflection devices (31) which the Reduce the speed of the fuel passing through and deflect the fuel in such a way that that this runs from the fuel atomizer (27) transversely to this. 2. Combustion chamber according to claim 1, characterized in that the downstream end of the fuel atomizer (27) over itself bent back to form a channel (31) for the fuel which forms the deflector is, and that the channel runs transversely to the fuel atomizer (27) and opposite at both Ends is open. 3. Combustion chamber according to claims 1 or 2, characterized in that the fuel atomizer (27) is curved radially inward towards the downstream end. 4. Combustion chamber according to one of the preceding claims, characterized in that in In a manner known per se, the combustion chamber (13) is designed in the shape of a circular ring and has several Fuel injection nozzles (26) are equipped, which are arranged in the circumferential direction at a distance from one another and each fuel injector (26) is equipped with a fuel impingement atomizer (27) is. 5. Combustion chamber according to claim 4, characterized in that in the annular combustion ao chamber (13) an annular arrangement of flow guide plates arranged at a distance from one another (34) is provided that the fuel atomizer (27) in the space between each adjacent pair of flow guide plates (34) is arranged and that the Guide plates (34) ensure that the combustion air is directed over the impact atomizer will. 6. Combustion chamber according to one of the preceding claims, characterized in that the Fuel atomizer consists of a plate (27). Considered publications:
Swiss Patent No. 246 172;
French Patent No. 1251 927;
British Patent No. 840529;
U.S. Patent No. 2,560,207. 1 sheet of drawings 509 689/109 9.65 © Bundesdruckerei Berlin