GB2035540A

GB2035540A - A gas turbine engine fuel injector

Info

Publication number: GB2035540A
Application number: GB7936526A
Authority: GB
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 1978-11-23
Filing date: 1979-10-22
Publication date: 1980-06-18
Also published as: GB2035540B

Abstract

A dual fuel injector for a gas turbine engine having means for water injection to reduce NOx emissions, comprises an outer annular gas fuel duct 44 with a venturi section 46 with air purge holes 50 to prevent liquid fuel entering the gas fuel duct, an inner annular liquid fuel duct 60 having inlets 34, 40 for liquid fuel and water respectively and through which compressor air flows, the inner annular duct 60 terminating in a nozzle 72, and a central flow passage 62 through which compressor air also flows, terminating in a main diffuser having an inner secondary diffuser 64. The surfaces of both diffusers are arranged so that their surfaces are washed by the compressor air to reduce or prevent the accretion to carbon to the injector, the diffusers in effect forming a hollow pintle 56. <IMAGE>

Description

SPECIFICATION Short title: Industrial RB 211 dual fuel burner Improvements in or relating to fuel injectors This invention relates to fuel injectors, for example, fuel injectors for gas turbine engines which are capable of running on a liquid fuel, a gaseous fuel or a mixture of liquid and gaseous fuels and in which both the accretion of carbon particles on the injector is minimised and the emission of the oxides of nitrogen is kept to an acceptable level.

The present invention provides a gas turbine engine fuel injector comprising a first body having duct means for a liquid fuel, duct means for a gaseous fuel and duct means for a water supply, a second body located within the first body, a first flow passage for the throughflow of compressed air in communication with the duct means for the liquid fuel and the water supply and having a central second flow path for the through flow of compressed air, having a downstream diffuser portion and flow directing means to direct a flow of air onto at least a part of the diffusing means.

The liquid fuel duct means may comprise a supply duct, a manifold and a plurality of holes drilled tangentially into the manifold, the fuel passing into the first flow passage being swirled thereby and forming a complete sheet of fuel on the wall of the first flow passage.

The gaseous fuel duct means may comprise a gas fuel duct, a partial gas annulus and an exit nozzle. Purge air inlet apertures may be provided in the wall of the first body adjacent the gas exit nozzles, the purge air, supplied from the compressor of the gas turbine engine of which the fuel injector forms apart, preventing liquid fuel from passing into the gas passages.

The water supply duct means may comprise a water supply duct, a manifold and a plurality of radially drilled holes into the manifold, the water supply holes being located upstream of the liquid fuel holes.

The first flow passage may narrow in crosssectional area towards its downstream end so that a fuel and air mixture or a fuel, air and water mixture in the first flow passage accelerates to a maximum at the exit or nozzle of the first flow passage where it will be sandwiched between air from the gas purge holes and air flowing through the second flow path thereby aiding the atomisation of the liquid fuel which had already undergone an atomising process as it passed into the first flow passage.

When water is injected into the first flow passage it also undergoes an atomisation process in a like manner to the liquid fuel.

The diffuser means of the second flow path may comprise a main diffuser and a secondary diffuser located within the main diffuser, the flow directing means conveniently comprising a plurality of flow directing apertures in a wall joining the upstream ends of the main and secondary diffusers, a gap being left between the inner wall of the main diffuser and the downstream end the secondary diffuser so that some of the compressed air flowing through the second flow path will flow through the flow directing apertures, through the said gap and wash over the inner wall of the main diffuser.

The present invention will now be more particularly described with reference to the accompanying drawings in which, Figure 1 shows a portion of a gas turbine engine including one form of fuel injector according to the present invention, Figure 2 shows a detailed sectional view of the fuel injector shown in Fig. 1, Figure 3 is a section on line 3-3 in Fig.

2, Figure 4 is a section on line 4-4 in Fig. 3 and, Figure 5 is a view on arrow A in Figure 1.

Referring to the Figures, a fuel injector 10 is located in a gas turbine engine only parts of which are shown, namely a casing 12, combustion equipment comprising an outer casing 14 and an annular combustion chamber 16, and a ring of nozzle guide vanes 1 8 which are located at the exit of a compressor (not shown).

The fuel injector 10 comprises a first body 20 and a second body 22 located within the first body, the first body having liquid fuel duct means 24, water supply duct means 26 and gaseous fuel duct means 28. The duct means 24 comprises a liquid fuel supply duct 30 connected to a fuel manifold which supplies fuel to all the injectors 10 of the engine, a manifold 32 and a plurality of tangentially drilled equi-spaced holes 34 (see Fig. 3). The duct means 26 comprise a water supply duct 36 connected to a water manifold (not shown) which supplies water to all the fuel injectors 10 of the engine, a manifold 38 and a plurality of radially drilled equi-spaced holes 40.The duct means 28 comprises a gaseous fuel duct 42 connected to a gas manifold (not shown) which supplies gaseous fuel to all the fuel injectors 10 of the engine, a part annulus 44 (see Figs. 3 and 4), a venturi portion 46 and a diffuser portion 48. The first body 20 also has a plurality of tangentially drilled holes 50 through its outer wall 52 in the region of the venturi portion 46, for the inflow of purge air from the engine compressor into the gaseous fuel duct.

The second body 22 comprises an outer ring 54 which is located within the first body between the outlets of the rows of holes 34 and 28, the ring 54 supporting a centreless pintle 56 by two webs 58. A first flow path 60 is defined by the first and second bodies 20, 22 and second flow path 62 is provided through the centre of the second body 22. The centreless pintle 56 comprises a main diffuser 62 and a secondary diffuser 64 which are joined together at their upstream ends by a wall 66, a gap 68 being provided between the inner wall of the main diffuser and the downstream end of the secondary diffuser. A plurality of holes 70 drilled in the wall 66 provide a flow directing means for air flowing through the second flow path 62.

In operation, liquid fuel flows through the duct 30 into the manifold .32 and through the tangential holes 34 into the first flow path 60, a complete sheet of fuel being formed on the outer wall of the flow path 60, the air from the compressor which flows through the first flow path shears the fuel from the holes 34 causing atomisation and the fuel and air mixture accelerates along the flow path as the flow decreases in cross-section to a minimum at its exit 72.

The mixture which passes from the fuel injector is also subject to a partial shear effect since the outflowing mixture will be sandwiched between an outer layer of air flowing from the purge holes 50 and an inner layer of air which has flowed through the path 62, the shear effect aiding the atomisation of fuel and water.

When a gaseous fuel is being burnt, the gas fuel passes from the gas manifold into the gas duct 42, the part annulus 44, the venturi portion 46, where purge air enters through the holes 50 and the diffuser 48. As the gase leaves the injector it is met by relatively high velocity air flowing out of the exit 72 which directs the gas fuel into the combustion chamber 16.

The purge holes 50 are provided to prevent liquid fuel from entering the gas fuel duct when the engine is running on liquid fuel, which would otherwise cause explosion and fires on changeover from liquid to gas fuel.

The purge air fills the gas duct and because the shape of the passage 48 is that of a natural diffuser, the air clings to the walls of the passage preventing entry to any liquid fuel. Additionally, the air flowing through the purge holes tends to break up the gas fuel flow into discrete jets and makes the gas flow more stable. Thus the gas flow is more like that from a conventional gas burner in which the gas is discharged from a nozzle through individual jets.

Nitrogen oxides (NOx) produced by the combustion of fuels in gas turbine engines are formed by the combination of nitrogen and oxygen in the combustion air, and from the combination of nitrogen in the fuel with oxygen from the combustion air. There are four basic methods of reducing NOx:- (i) by reducing the combustion pressure (ii) by decreasing the peak flame temperature (iii) by reducing the effective residence time during which the combustion gases remain at elevated temperatures and (iv) by controlling the the amounts of nitrogen and oxygen available for the production of NOx. The present invention approaches the problem of NOx suppression by water injection, the water being introduced via the fuel injector.

The method requires water to be injected into the combustion process to provide a heat sink, which absorbs some of the heat produced by the combustion of fuel and air, thereby reducing peak combustion temperatures and the rate of NOx formation. The degree of NOx reduction depends upon the rate and method of introducing water, the best results being obtained by direct injection of atomised water into the primary zone of the combustion chamber.

In the present arrangement this is achieved by water fed from a manifold through the duct 36, into the manfiold 38. The water is then introduced to the compressor air in the flow path 60 using the cross stream injection principle through the holes 40 where the water is atomised, this method having the advantage of a uniform circumferential pattern and a minimum length requirement. The internal shape of the flow path 60 is such that the majority of the water is atomised through the exit 72 of the injector to be mixed directly with the fuel in the primary zone of the combustion chamber. Only high purity water must be used for this method in order to minimise corrosion of engine components. NOx emissions can be reduced by between 7090% using a 1:1 water/fuel ratio, although there may be a reduction of up to 1.0% in gas turbine efficiency.

The centreless pintle 56 has been specifically designed to cope with the problem of carbon accretion on the fuel injector. In all combustion operations in gas turbine engines a certain amount of carbon is produced in the process, and some of the carbon will build up on certain areas of the injector. When the carbon builds up to a certain height it breaks away from the injector and travels through the combustion chamber to the turbine, where it can cause erosion of the turbine blade leading edges, or even a total blade failure.

The present design has attempted to alleviate this problem by initially reducing as far as is possible, the surface area available to which the carbon can adhere and where this solution was not possible to wash those surfaces to which carbon could adhere, with air from the engine compressor.

In the centreless pintle 56, compressor air flows along the flow path 62 and washes the inner surface of the secondary diffuser 64 and at least some of the inner wall of the main diffuser 62 by natural diffusion. The remaining compressor air flows through the ring of holes 70 and then through the annular gap 68 so that the entire inner wall of the main diffuser 62 can be washed with compressor air. By this means, carbon accretion on the fuel injection may be reduced to an acceptable level, at which although some carbon may adhere, it will break off in relatively small pieces which would not damage downstream engine components.

Claims

1. A gas turbine engine fuel injector comprising a first body having duct means for a liquid fuel, duct means for a gaseous fuel and duct means for a water supply, a second body located within the first body, a first flow passage for the throughflow of compressed air in communication with the duct means for the liquid fuel and the water supply and having a central second flow path for the throughflow of compressed air, having a downstream diffuser portion and flow directing means to direct a flow of air onto at least a part of the diffusing means.

2. A fuel injector as claimed in claim 1 in which the liquid fuel duct includes a manifold and a plurality of holes formed tangentially to the manifold, the liquid fuel passing from the manifold into the first flow passage via the tangential holes.

3. A fuel injector as claimed in claim 1 in which the first flow passage decreases in cross-sectional area towards its downstream end, the minimum cross-sectional area of said first flow path being at the downstream extremity thereof.

4. A fuel injector as claimed in claim 1 in which the gaseous fuel duct means includes an annular duct located around the first flow passage, a portion of said annular passage being of reduced cross-section area, air purge apertures being provided in the region of said reduced cross-sectional area.

5. A fuel injector as claimed in claim 2 in which the water supply means includes a manifold having a plurality of holes into the first flow passage, the water supply holes being located upstream of the tangential fuel holes.

6. A fuel injector as claimed in claim 1 in which the diffuser means comprises a main diffuser and a secondary diffuser located internally of the main diffuser.

7. A fuel injector as claimed in claim 1 in which the flow directing means comprises a plurality of flow directing apertures in a wall joining the main and secondary diffusers, and an annular gap between the inner wall of the main diffuser and the outer wall of the secondary diffuser.

8. A gas turbine engine fuel injector having a central flow passage terminating in diffuser means, for the throughflow of compressed air, an inner annular flow passage for the throughflow of compressed air and liquid fuel, the said inner annular flow passage terminating in an annular nozzle, and an outer annular flow passage for the throughflow of gaseous fuel, the said outer annular flow pasaage having a portion of reduced crosssectional area and purge air inlet apertures in the region thereof.

9. A fuel injector as claimed in claim 8 in which the diffuser means comprises a main diffuser and a secondary diffuser located therein, the said diffusers being joined together at their upstream ends by a wall, the wall having a plurality of apertures and a gap being provided between the downstream end of the secondary diffuser and the main diffuser, compressed air being able to flow through the centre of the secondary diffuser and over the inner wall of the main diffuser via the said apertures and gap and the secondary diffuser.

10. A gas turbine fuel injector constructed and arranged for use and operation substantially as herein described with reference to and as shown in the accompanying drawings.