JPS6153424A - Fuel injection valve for gas turbine - Google Patents

Abstract

PURPOSE:To solve a shortage of air as well as to aim at a complete combustion, by installing a guide vane giving a swirl to air, while installing an injection port, jetting an air-fuel mixture outward aslant inside a combustor, and another injection port jetting air alone in a center direction inside the combustor either. CONSTITUTION:A nozzle outer tube 21 of a fuel injection nozzle 20 is attached to one end wall in an axial direction of an inner tube 23 of a gas turbine combustor 22. And, fuel atomizing air A is drawn in from a suction port 30 installed in a nozzle inner tube 24 and, after a swirl is given by a guide vane 33, it is divided into an outer flow passage 35 and an inner flow passage 36. An air A3 flowing in the outer flow passage 35 is mixed with fuel F out of an outflow port 27, making up it into an air-fuel mixture G4, and it is jetted outward aslant inside the combustor 22 from an injection port 37. On the other hand, air A4 flowing in the inner flow passage 36 is divided into air A5 to be jetted to a center direction inside the combustor 22 from an injection port 38 and another air A6 to be jetted outward aslant inside the combustor 22 from a hole 39 of a guide tube 32.

Description

DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a fuel injection valve for a gas turbine that mixes gas turbine fuel with air and injects the mixture into a gas turbine combustor.

(Prior art) Figure 3 shows this type of conventional fuel Fl injection for gas turbines.
t.

In FIG. 3, reference numeral 1 denotes a fuel injection nozzle, and a sled nozzle outer cylinder 2 is attached to an inner cylinder 4 of a gas turbine combustion chamber 03. In addition, 5 is a nozzle inner cylinder, and a stay 6 is located in the center of the nozzle inner cylinder.
Pintorua is being investigated through.

Now, the compressed air A sent into the nozzle l from the compressor (not shown) is divided by the nozzle inner cylinder 5, and is divided into a flow path 8 between the nozzle outer cylinder 2 and the nozzle inner cylinder 5, and a flow path 8 between the nozzle outer cylinder 2 and the nozzle inner cylinder 5. 5 and the inner flow path 9.

At this time, the fuel F introduced from the fuel supply port 10 passes through the fuel flow path 11 and flows out from the outlet 12, mixes with the air A1 passing through the flow path 9, and becomes mist. Then, the air-fuel mixture G1 mixed with the fuel F merges with the air A2 from the flow path 8 before the injection 1113, becomes the air-fuel mixture G2, and enters the combustor 3 from the injection port 13 diagonally in the radial direction. Squirt outward.

Further, air A that is separately sent from outside the nozzle 1 is given a swirl by a guide vane 14 provided between the nozzle outer cylinder 2 and the combustor inner cylinder 4.

It flows into the combustor 3. Then, this swirling air A and the mixture % G 2 ejected from the nozzle injection port 13 merge,
The fuel F in this mixture G2 is further diluted and diffused.

By the way, a part of the air-fuel mixture G2 spouted into the combustor 3 is
As shown by arrow G3, it circulates near the front of the pin lure. This air-fuel mixture G3 has a high concentration because it is not diluted by the air A swirling by the guide vane 14. Therefore, near the front of the pin lure, there is a lack of air, that is, fuel tends to be excessively stripped, which tends to cause incomplete combustion.

Further, since the air A1 does not have a strong swirl, the fuel F led out from the outlet 12 is not sufficiently mixed with the air AI and is ejected into the combustor 3. Therefore, in this respect as well. Incomplete combustion is more likely to occur.

For this reason, the Now in the exhaust gas is caused by the incomplete combustion described above.
The disadvantage is that the content of harmful substances such as , Co and HC increases. In addition, carbon generated by incomplete combustion not only accumulates on the front surface 7a of the pin lure, but also is blown off and adheres to the gas turbine (r; 4 not shown), causing clogging of the gas turbine. .

(Object of the Invention) This invention has been made in order to solve the above-mentioned drawbacks, and to sufficiently mix fuel into the air.

By resolving partial air shortages in the combustor and eliminating incomplete combustion of fuel, it is possible to reduce the content of harmful substances in exhaust gas, and also to reduce the amount of carbon deposited in incomplete combustion areas. It is an object of the present invention to provide a fuel injection valve for a gas turbine that can prevent carbon from clogging the gas turbine.

(Structure of the Invention) In order to achieve the above object, the present invention provides a fuel injection valve for a gas turbine, in which a guide vane for swirling the air is provided in the nozzle, and the air-fuel mixture mixed with fuel is The combustor is configured to include an injection port that injects the air obliquely outward in the radial direction inside the combustor, and an injection port that injects only air toward the center of the combustor, so that the fuel is sufficiently mixed into the air, and This eliminates the partial air shortage within the combustor and prevents incomplete combustion of the fuel.

(Embodiment) FIG. 1 shows a fuel injection valve for a gas turbine according to an embodiment of the present invention.

In FIG. 1, 20 is a fuel injection nozzle, and its nozzle outer cylinder 21 is attached to one axial end wall of an inner cylinder 23 of a gas turbine combustor 22. In FIG. 24 is a nozzle inner cylinder, and a plurality of axial grooves 25 are formed on its outer surface.
The exterior portion 26 is bonded by welding or the like. Furthermore, an outlet 27 is provided at the tip of the groove 25 . Furthermore, an annular groove 28 is formed in a portion of the inner surface of the exterior portion 26 that faces the base end of the groove 25 .

Further, the exterior portion 26 is provided with a fuel supply port 29 that communicates with the groove 28 . Therefore, the fuel F introduced from the fuel supply port 29 is transferred to the annular groove 28 and the cell 11.
passing through the groove 25 in the direction.

The liquid is led out from the outlet 27 into the nozzle 20 .

Furthermore, an air inlet 30 for air A is provided in the nozzle inner cylinder 24 and the exterior part 26.

31 is a primary nozzle, which is provided inside the nozzle 20 and concentrically with this nozzle 20, and its tip 31a
A guide cylinder 32 for air A is attached to the cylinder via a stay (not shown). Further, a guide vane 33 is provided between the plastic primary nozzle 31 and the nozzle inner cylinder 24 to give the air A a swirl. Here, the fuel Fl of the primary nozzle 31 is separately fed from its base end 31b. 34 is a casing outer cylinder.

Now, the fuel*1 atomization air A taken in from the air intake port 30 is given a swirl by the guide vane 33, and then
The guide tube 32 divides the flow into a flow path 35 outside the guide tube 32 and a flow path 36 inside the guide tube 32 .

The air A3 flowing through the flow path 35 is mixed with the fuel F led out from the outlet 27, and the air mixture G4 is ejected from the injection port 37 into the combustor 22 diagonally outward in the radial direction. In addition, the air A4 flowing through the flow path 36 is injected through the air A5 which is ejected from the primary nozzle 38 toward the front of the primary nozzle 31, that is, toward the center of the combustor 22, and the air A4 which passes through the holes 39 provided in the guide cylinder 32. 39 and air 86 which is ejected diagonally outward in the radial direction within the combustor 22.

In this way, since the injection port 38 for ejecting air As also toward the center of the combustor 22 is provided, the primary nozzle 31
The lack of air near the front of the guide tube 32 is eliminated. Further, since the air A3 is given a swirl by the guide vane 33, the path of fuel mixing becomes longer, and the fuel F is sufficiently mixed into the air A3. Therefore, incomplete combustion of the fuel F is eliminated, so that carbon is prevented from being deposited on the front surface of the primary nozzle 31 and the guide tube 32, and this carbon adheres to the gas turbine (not shown). This prevents clogging. Furthermore, since incomplete combustion is eliminated, the content of harmful substances in the exhaust gas is reduced.

Here, in the embodiment shown in FIG. 1 described in Section 2, a nozzle is shown in which the primary nozzle 31 and the air A flow path 35, 36 are formed by the idle cylinder 32, but the same type as the conventional example shown in FIG. 3 is used. FIG. 2 shows an embodiment in which the present invention is applied to a nozzle.

In FIG. 2, the same parts as in FIG. 3 are given the same reference numerals, and detailed explanation thereof will be omitted.

As shown in FIG. 2, a guide tube 4z is attached to the bottle 40 via a stay 41. As shown in FIG. and an injection port 43 that injects the air-fuel mixture G5 mixed with the fuel F obliquely outward in the radial direction within the combustor 3 through the guide tube 42;
An injection port 44 that injects air A2 toward the center of the combustor 3
is formed. Further, this guide tube 42 is provided with a large number of holes 45, and air 88 is also blown out from these holes 45. Further, a guide vane 46 is provided between the bottle 40 and the nozzle inner cylinder 5.

In this way, also in the embodiment of FIG. 2, the combustor 3
An injection port 43 that injects the air-fuel mixture G5 diagonally outward in the radial direction.
and an injection port 44 for ejecting air A2 toward the center of the combustor 3, the lack of air near the front of the bottle 40 is eliminated.

Further, since the air is swirled by the guide vanes 46, the fuel is sufficiently mixed into the air. Therefore, incomplete combustion is eliminated, and the same effect as the embodiment shown in FIG. 1 is achieved.

(Effects of the Invention) As explained above, according to the present invention, the fuel is sufficiently mixed into the air, and the partial air shortage in the combustor is resolved, thereby eliminating incomplete combustion of the fuel. This fuel injection valve for gas turbines not only reduces the content of harmful substances in exhaust gas, but also prevents carbon from accumulating in incomplete combustion areas and clogging the turbine. can be provided.

[Brief explanation of drawings]

FIG. 1 is a sectional view showing a fuel injection valve for a gas turbine according to one embodiment of the present invention, FIG. 2 is a sectional view showing another embodiment, and FIG. 3 is a sectional view showing a conventional fuel injection valve for a gas turbine. FIG. 1.20...-nozzle, 3.22... combustor, 33.
44...Guide vane, 37.38.43.44...Injection 1, A...Air, F...Fuel, G...Mixture. Fig. 1 1L Fig. 2

Claims (1)

[Claims] (1) In a gas turbine fuel injection valve that mixes fuel with air in a nozzle attached to one end wall in the axial direction of the combustor to create a mixture, and injects this mixture into the combustor, the air A guide vane is provided in the nozzle to give a swirl, and an injection port is provided to inject the air-fuel mixture mixed with fuel diagonally outward in the radial direction within the combustor, and only air is injected toward the center of the combustor. A fuel injection valve for a gas turbine, characterized by comprising an injection port.