JPH04502355A - Turbine engine with pin injector - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] Turbine engine with pin injector The present invention is particularly useful in gas turbine engines, in which fuel spray pinpointing is used to improve reliability. The present invention relates to a gas turbine engine having a zector.

1st grade Gas turbine engines are used to maintain turbine operation under a variety of operating conditions. It has a fuel injector that can be used. A relatively small type of aircraft used in flight situations. In turbine engines, the fuel flow at high altitudes is often very low; This is because a typical volute pressure spray starting fuel injector is Very low fuel flow required at altitudes as high as ,000 feet), e.g. For example, fuel spray that does not inject at a flow rate below 1.362 kg/hour (3 bonds/hour) cause problems. For high altitude ignition of gas turbine engines, the combustor vessel The product must be maximized, i.e. to allow sufficient time for the reaction. In addition, a combustor must be constructed to be effective for combustion in cold and high altitude conditions. The high fuel viscosity that occurs adds even more difficulty to achieving reliable operation.

Furthermore, ignition is relatively easy at low engine speeds, which are only 10% of maximum engine speed. , but the dynamic loads are significantly increased by engine acceleration. like this Under conditions, the blow-off occurs at particularly high speeds, so the resulting poor distribution of fuel is dynamic. No matter how important the problem is when representing a load, e.g. combustion difficulties, the volute pressure It is most important to avoid partial overfueling of the atomizing type common starting injector. . It is also particularly effective at low speeds, as fuel evaporation problems do not further complicate operating difficulties. Providing good fuel spray is even more important at the main fuel injector.

The present invention is directed to solving one or more of the problems mentioned above.

11mu■j The primary purpose of this invention is to provide a new and improved turbine engine that increases reliability. It's about doing. In particular, it is an object of this invention to provide a device design that can be manufactured at low cost. Turbine engine with excellent fuel atomization to ensure reliable high altitude operation The object of the present invention is to provide a new and improved fuel injection system for the engine. Another object of this invention is for providing a fuel supply conduit that directs fuel against a fuel impingement surface within an air conduit. Ru.

A preferred embodiment of the invention is a gas combustion engine having an annular combustor forming an annular combustion chamber therein. The above objectives are achieved in a turbine engine. The annular combustor is an interlocking fuel It includes at least one igniter mounted together with the injector. fuel injection The device injects a mixture of fuel and air into an annular combustion chamber for ignition by an igniter It can be done like this. In particular, the fuel injector is connected to a source of fuel and to a source of pressurized air. It has a fuel pipe installed within the connected air pipe.

This configuration allows the air tube to have an exit orifice in communication with the annular combustion chamber. It is composed of Also, the fuel pipe is located within the air pipe upstream of the air pipe outlet orifice. A feature of the present invention is that it has an exit orifice.

In the preferred embodiment, the air and fuel tubes are cylindrical and the exit orifice of the fuel tube is is provided concentrically and spaced apart from the outlet orifice of the air tube, and the impact surface It is located in the middle of the hundred orifice. The air pipe carries air from the fuel injector and an outlet orifice of smaller dimensions than the main air passage to accelerate the fuel mixture It preferably has a main air passageway extending towards and terminating at. Furthermore, the fuel pipe is An outlet of similar dimensions smaller than the main fuel passage to produce acceleration of the fuel from the fuel tube. It has a main fuel passage extending and terminating at the mouth orifice.

In another embodiment, the exit orifice of the fuel tube is a constant for fuel flowing through the fuel tube. It has the same dimensions as the main fuel passage to provide speed.

The fuel is placed in the path of the fuel ejected from the fuel tube, such as at the impact surface. Preferably formed by the end of a pin placed concentrically with the exit orifice of the tube It is. The pin can be supported by an air pipe or a fuel pipe, but in either case the air facing the exit orifice of the tube) to produce a cone-shaped spray or film. The outlet orifice of the fuel tube is made of the same shape and dimensions.

Additionally, the end of the pin substantially directs the flow of fuel through the outlet orifice of the fuel tube. spaced apart from the fuel pipe outlet orifice to completely block the .

Other objects, features and advantages of the invention may be found in the following detailed description in conjunction with the accompanying drawings. It will become clear.

of t・ FIG. 1 is a somewhat schematic cross-sectional view of a turbine engine embodying the invention; FIG. 1a is a diagram showing another embodiment of the fuel pipe of the turbine engine of FIG. 1; 1 bll is a somewhat schematic cross-sectional view of a portion of the turbine engine in section 1; FIG. 2 is a sectional view of another embodiment of the pin support of the turbine engine of FIG. 1; FIG. 3 is a graph showing the dynamic loads of a turbine engine of the type shown in FIG. It is.

A lot of things to do.

A preferred embodiment of a gas turbine constructed in accordance with this invention is a radial breather gas turbine. Shown in the drawing in the form of a bottle. However, this invention is limited to radial flow gas turbines. First, it can be applied in the form of an air-breathing turbine with an annular combustor.

Referring to FIG. 1, reference numeral 1o indicates an annular combustor forming an annular combustion chamber 14 therein. 12 shows a gas turbine engine with 12. Most of Figure 1 is general. Although not all of the various working components of a gas turbine engine are shown, the installed By using a cross-sectional view of an annular combustor 12 with at least one igniter 16. It will be obvious that this is a unique feature of the engine. includes an associated fuel injector to inject a mixture of fuel and air into the annular combustor 12. have.

In particular, the fuel injector injects a mixture of fuel and air for ignition by the igniter 16. The fuel injector has a spray nozzle 18 adapted to inject fuel into the combustion chamber 14. . The fuel injector spray nozzle 18 includes a plurality of fuel injector spray nozzles communicating with an air source, which will be described in detail later. has an opening 21 and an outlet orifice 22 communicating with the annular combustion chamber 14. an air pipe 20, and a fuel provided in the air pipe 2o and connected to a fuel source (not shown). The fuel tube 24 has an outlet orifice 22 within the air tube 20. It has an upstream exit orifice 26. Referring to Figures 1 and 2, the fuel The injector injection nozzle 18 is located in the air opposite the outlet orifice 26 of the fuel pipe 24. It has a fuel impingement surface 28 within the trachea 20 .

As is clear from FIG. 1, the air pipe 2o and the fuel pipe 24 have a circular cross section in the axial direction. Ru. Also, an outlet orifice 26 of the fuel pipe 24, suitably described as a fuel supply pipe. is arranged so as to be concentric with the outlet orifice 22 of the air pipe 20. With this configuration, the collision surface 28 is located between the air pipe 20 and the fuel supply pipe 24. The outlet orifices 22, 26 are located in the middle of each other.

More specifically, the air tube 20 extends and terminates at an outlet orifice 22. It has a main air passage 30.

The outlet orifice 22 of the air tube 20 allows air from the fuel injector spray nozzle 18 to smaller than the main air passage 30 to accelerate the mixture of fuel and fuel, FIGS. In the embodiment shown in Figure 1b, the addition of the fuel as it exits the fuel supply pipe 24 is The outlet orifice 26 of the fuel supply pipe 24 is located above the main fuel passage 32 so as to It will be noted that the fuel supply pipe 2o is also smaller, as is the case with the air pipe 2o. 4 is formed such that the main fuel passage 32 extends toward and terminates at the outlet orifice 26. ing.

In another embodiment shown in FIG. 1a, the fuel tube 24'° has an outlet orifice 26°. It extends in both directions and ends. However, in this embodiment, the exit orifice 26' is It has the same size as the fuel passage 32°, which allows the fuel to flow through the fuel supply pipe 24. ′ at a completely constant flow rate.

1 and 1b, the impact surface 28 is located at one end of the bin 34. It is formed by points.

One end of the bin 34 is located concentrically and spaced apart from the outlet orifice 26 of the fuel tube 24. It is understandable that you are being rejected.

Additionally, one end of the bottle 34 is configured to substantially completely block fuel from the fuel supply line 24. (see Figure 1b).

In particular, the bottle 34 is connected to the air pipe 20 as will become apparent by special reference to FIG. It can be supported suitably. At least the end of the bottle 34 forming the impact surface 28 It is preferably configured to have substantially the same dimensions as the outlet orifice 26 of the feed pipe 24. subordinate Thus, the end of the bottle 34 is oriented at 3 towards the outlet orifice 22 of the air tube 20. As shown in Figure 6, the fuel produces a cone-shaped spray, or film (see Figures 1 and 6). See Figure 1b.

Also, the bottle 34' is suitable for use with the fuel pipe 24, as will be apparent by reference to FIG. can be supported. However, this is substantially the same as the outlet orifice 26 of the fuel supply pipe 24. Suitable for the end forming the impact surface 28' of the bin 34' to be configured in one dimension It is. As before, the end of the bottle 34' points toward the outlet orifice 22 of the air tube 20. The oriented fuel forms an f-cone shaped spray or film.

With particular reference to FIG. has a generally formed body. This body is designed to control the air inside the combustor annulus 37. a radial direction having an opening 21 communicating with the source and including a restricted exit orifice 22; It has a beam cylindrical wall 20a terminating in an inwardly facing end cap 20b, as shown in FIG. As shown, at 38 a fuel tube 24 can be supported which can pass through the cylindrical wall 20a. Ru. Also, as shown, the bottle 34 can be secured by conventional means such as welding or similar means. can be supported by a radially inwardly facing end cap 20b at 40.

As shown in FIG. 2, in the illustrated embodiment, the bottle 34 is cylindrical at 42. It can be supported in a similar manner by a cylindrical wall 24a, which cylindrical wall 24a including an exit orifice 26 restricted to form a radially inwardly directed It ends at the end cover 24b. In either case formed by bin 34 or 34° The fuel impingement surface 28 or 28° is the exit orifice of the fuel tube 24 or 24'. 26 or 26' concentrically and of substantially the same shape and dimensions and further spaced apart. It is set up in the same condition.

As can be seen, the fuel injector injection nozzle 18 is a separate impingement type main fuel injector. has. Fuel is routed through fuel tube 24 or 24' to outlet orifice 26 or 2. 6゛ is supplied. This exit orifice 26 or 26' has a minimum pressure drop and The maximum orifice size allows for a sharp edge as shown in Figure 1, but if If manifold head compensation is to maximize combustion at very high altitudes, then (see Figure 1a). In any case , the fuel jet 44 is concentric and substantially identical to the outlet orifice 26 or 26'. A circular bottle 34 or 34° in diameter collides with how suitable.

1.362 kg/kg of very high viscosity (30 centistokes and above) fuel at a very small fuel flow rate with a value of O-7 kg/am' (1 Even at low fuel pressures (0 psi) and below, the beam-conical fuel injection A fog or film 36 is formed. Common films are bubbles, i.e. The fuel spray looks like a very thin film (see Figure 1b). Under normal conditions, the swirling chamber of the vortex fuel injector Very good fuel atomization is achieved since there are no viscous losses such as those encountered within the fuel tank.

Unlike the swirl injector, the fuel injector injection nozzle of this invention makes a very high energy conversion from Particularly good fuel atomization at low fuel pressures, small fuel flows and high viscosity is achieved.

Most importantly, air flows through air tube 20 and forms air/fuel jets 46. by the atomized fuel passing through the outlet orifice 22 to create what can be described as The inner and outer combustor walls 48a forming the combustor annular portion 37 are accelerated (see FIG. 1); 48b, or in the dome of the combustor, the outlet orifice 22 of the air tube 20 is angled. The fuel injector injection nozzle 18 is removed by a sliding fit such that the fuel injector injection nozzle 18 is The air/fuel jets 46 are attached to the flange of the annular combustor 12. It will be understood that the flame has a partially circumferential trajectory around the flame region, With this configuration, when air passes through the outlet orifice 22 of the air tube 20, the air It is accelerated from a relatively low speed V to a relatively high speed v2.

As is clear, the speed V3, ■2 depends on the special application, relative dimensions and air and fuel pressures. It is based on various parameters including, etc. However, the velocity of the air is the fuel film 3 It is only noted that the criterion is that it must be sufficient to block 6. Should. This is such that ignition can be achieved under a wide range of operating conditions. The highly possible atomization of fuel that can be achieved with the device of this invention.

In addition, the current air speed of 22.73 m/s (75 ft/s) is even lower. It should be noted that temperatures below 50°C may be sufficient for low speed starting applications. Therefore , the fuel injector injection nozzle 18 eliminates the need for a separate starting injector. It can be configured to act as a main fuel injector.

When the engine is accelerated through a limited maximum dynamic load condition Ws (Fig. 3), the A larger fuel flow will result in further improvement of the spray, therefore less fuel flow as in the past. At full speed conditions, there will be no obstruction to combustion as a result of lack of fuel based on evaporation. In this case, a particularly fine fuel spray is achieved using only fuel pressure.

Furthermore, the high velocity airflow ensures very rapid fuel evaporation and optimal fuel atomization. A very slow exhaust gas is achieved.

While the foregoing description has described preferred embodiments of the invention, the scope of the appended claims It is clear that this invention should be limited only by the true spirit and scope of the invention. AroFIG, 3 international search report

Claims (20)

[Claims] 1. a body having an air tube and an outlet orifice connected to a source of pressurized air; An outlet orifice inside the air tube upstream of the air tube outlet orifice connected to the fuel source fuel in the air pipe opposite the outlet orifice of the fuel pipe; collision surface, Fuel injector injection nozzle with. 2. The air and fuel tubes are approximately cylindrical and approximately concentric with the air tube exit orifice. The exit orifice of the fuel pipe is arranged so that the collision surface is the exit orifice of the air pipe. The fuel inlet according to claim 1, which is provided between the outlet orifice and the fuel pipe. Zekta injection nozzle. 3. The air tube extends toward and terminates at the outlet orifice of the air tube. The outlet orifice of the air tube has a main air passageway with a claim having dimensions smaller than the main air passageway so as to accelerate the mixture of ingredients; 2. The fuel injector injection nozzle according to item 2. 4. The fuel tube extends toward and terminates at the outlet orifice of the fuel tube. The outlet orifice of the fuel tube has a main fuel passage that is Claimed to have dimensions smaller than the main fuel passage so as to accelerate the fuel mixture A fuel injector injection nozzle according to range 2. 5. The fuel tube extends toward and terminates at the outlet orifice of the fuel tube. The outlet orifice of the fuel tube has a main fuel passageway that is be of the same dimensions as the main fuel passage to provide a constant velocity for the fuel. The fuel injector injection nozzle according to claim 2. 6. The impingement surface is formed by the end of the bin, which is connected to the fuel pipe and the outlet orifice. The fuel is placed concentrically and spaced apart from the fuel pipe, and the fuel is The fuel inlet according to claim 2, which is dimensioned to provide a qualitatively complete shut-off. Zekta injection nozzle. 7. forming an annular combustion chamber therein, and at least one igniter or igniter mounted therein; an annular combustor having an internal fuel injector and an associated fuel injector; for injecting a mixture of fuel and air into the annular combustion chamber for ignition by an igniter. an outlet orifice connected to a source of pressurized air and in communication with the annular combustion chamber; an air pipe having an outlet orifice connected to a fuel source and having an outlet orifice of the air pipe; a fuel tube within the air tube having an outlet orifice in the air tube on an upstream side; and a fuel tube within the air tube; a gas having an outlet orifice and a fuel impingement surface within the air tube in opposing relationship; turbine engine. 8. The air and fuel tubes are generally cylindrical, and the outlet orifice of the fuel tube is located at the outlet of the air tube. The outlet orifice of the air tube is positioned so that the fuel impingement surface is approximately concentric with the outlet orifice. Claim 7: Provided between the orifice and the outlet orifice of the fuel pipe. The gas turbine engine described. 9. The air tube has a main air passage extending and terminating at the outlet orifice of the air tube. and the outlet orifice of the air tube contains a mixture of air and fuel from the fuel injector. claim 1, which has smaller dimensions than the main air passage to accelerate the compound. Gas turbine engine according to item 8. 10. The fuel tube has a main fuel tube extending and terminating at the outlet orifice of the fuel tube. a passageway, and an outlet orifice of the fuel tube for accelerating fuel from the fuel tube. 9. A gas turbine according to claim 8, which has dimensions smaller than said main fuel passage. engine. 11. The fuel tube has a main fuel tube extending and terminating at the outlet orifice of the fuel tube. the outlet orifice of the fuel tube establishes a constant velocity of fuel passing through the fuel tube. 9. The fuel passage according to claim 8, wherein the fuel passage has substantially the same dimensions as the main fuel passage. Starbine engine. 12. The impingement surface is formed by the end of the bin, which end meets the outlet orifice of the fuel pipe. concentrically and spaced apart from the fuel pipe, and the end of the bin extends from the fuel pipe. Claim 8 is sized to substantially completely cut off fuel from the fuel. gas turbine engine. 13. The bottle is supported by an air tube, and at least one end of the bottle is connected to the outlet of the fuel tube. having the same shape and dimensions as the orifice, the end of the bin being connected to the outlet opening of the air tube. Claim 12 forming a generally conical spray of fuel directed towards the orifice. The gas turbine engine described in Section 1. 14. A bottle is supported by a fuel tube, and at least one end of the bottle is connected to an outlet of the fuel tube. The end of the bottle is approximately the same shape and dimensions as the orifice, and the end of the bottle is located at the exit of the air tube. Claim 1 forming a generally conical spray of fuel directed toward the mouth orifice. The gas turbine engine according to item 12. 15. at least one internally mounted igniter defining an annular combustion chamber therein; and an annular combustor having an associated fuel injector, the fuel injector having an internal for injecting a mixture of fuel and air into the annular combustion chamber for ignition by an igniter in the annular combustion chamber; an outlet opening connected to a source of pressurized air and in communication with the annular combustion chamber; an air tube having a orifice and an outlet orifice of the air tube connected to a fuel source; a fuel tube within the air tube having an outlet orifice in the air tube upstream of the fuel tube; a fuel impingement surface within the air tube in opposing relationship with an outlet orifice of the tube; The air tube and fuel tube are generally cylindrical, and the outlet orifice of the fuel tube is the outlet of the air tube. orifice and the exit orifice of the fuel tube, and the impingement surface is located at the end of the bin. and the end of the bin is concentric with and spaced apart from the outlet orifice of the fuel tube. and the end of the bin substantially absorbs fuel from the fuel tube. A gas turbine engine with dimensions such that it is completely shut off. 16. The air tube has a main air tube extending and terminating at the outlet orifice of the air tube. The air tube has an outlet orifice for mixing air and fuel from the fuel injector. The main fuel passage has dimensions smaller than the main fuel passage so as to accelerate the object. The gas turbine engine according to item 15. 17. The fuel tube has a main fuel tube extending and terminating at the outlet orifice of the fuel tube. a passageway, and an outlet orifice of the fuel tube is configured to provide acceleration of fuel from the fuel tube. 16. The gas turbine of claim 15, wherein the gas turbine has the same dimensions as the main fuel passage. engine. 18. The fuel tube has a main fuel tube extending and terminating at the outlet orifice of the fuel tube. a passageway, the outlet orifice of the fuel tube providing a constant velocity of fuel through the fuel tube; The gas star according to claim 15, wherein the gas star has the same dimensions as the main fuel passage. bin engine. 19. The bottle is supported by an air tube, and at least one end of the bottle is connected to the outlet of the fuel tube. The end of the bottle is approximately the same shape and dimensions as the orifice, and the end of the bottle is located at the exit of the air tube. Claim 1 forming a generally conical spray of fuel directed toward the mouth orifice. The gas turbine engine according to item 15. 20. A bottle is supported by a fuel tube, and at least one end of the bottle is connected to an outlet of the fuel tube. The end of the bottle is approximately the same shape and dimensions as the orifice, and the end of the bottle is located at the exit of the air tube. Claim 1 forming a generally conical spray of fuel directed toward the mouth orifice. The gas turbine engine according to item 15.