JPH06159089A - Gas turbine engine - Google Patents

Abstract

PURPOSE:To restrain fuel from being excessively fed, and thereby prevent the occurrence of blowoff in a main combustion chamber. CONSTITUTION:An air flow path expansion section 39 is formed at one part of air flow paths 36 and 37 so as to allow the flow speed of air 6 within the air flow path expansion section 39 to be lowered, blowoff in an auxiliary combustion liner 40 is prevented by providing the auxiliary combustion liner 40 equipped with a fuel infection nozzle 45 for the air flow path expansion section 39, and blowoff in the main combustion liner 38 can thereby be prevented by keeping flame generated in the auxiliary combustion liner 40 coming in the main combustion line 38 at all times.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention relates to a gas turbine engine.

[0002]

2. Description of the Related Art FIGS. 2 and 3 show an example of a conventional gas turbine engine.

In FIG. 2, 1 is a gas turbine engine body,
Reference numeral 2 is an inlet diffuser that constitutes the gas turbine engine body 1, 3 is an engine outer cylinder connected to the rear end side of the inlet diffuser 2, and 4 is an exhaust nozzle portion connected to the rear end side of the engine outer cylinder 3.

5 is provided inside the inlet diffuser 2,
It is a low-pressure compression unit having a suction fan 7 for sucking the air 6 and a vane 8.

Reference numeral 9 denotes a partition tube main body which is provided in front of the inside of the engine outer tube 3 and forms a bypass flow passage 10 between the engine outer tube 3 and the engine outer tube 3.
Front partition tube 11, central partition tube 12, rear partition tube 1
It is composed of 3.

Reference numeral 14 is a high-pressure compression section comprising a compression fan 15 for compressing the air 6 and stationary vanes 16 inside the front partition cylinder 11, and is provided adjacent to the low-pressure compression section 5. ing.

Reference numeral 17 denotes an annular combustion chamber provided on the inner peripheral portion of the central partition 12 and the combustion chamber 17 is shown in FIG.
As shown in FIG. 5, the air inlet 12a and the air flow passage 12b, into which the air 6 compressed by the high-pressure compression unit 14 flows, are provided on the upstream side, and the air 6 flowing through the air flow passage 12b is provided inside. A liner 18 having an air introduction hole 18a for introducing the fuel is provided inside the liner 18.
Fuel injection nozzle 2 for injecting fuel 20 from 9
1 and a vane 22 that surrounds the fuel injection nozzle 21 and applies a swirling force to the injected fuel 20.

Reference numeral 23 is a combustion gas generated in the combustion chamber 17.

Further, reference numeral 24 shown in FIG. 2 is provided in front of the inside of the rear partitioning cylinder 13, and the combustion gas 23 generated in the combustion chamber 17 causes the compression fan 1 of the high-pressure compression unit 14 to operate.
Compressor drive turbine 25 for driving 5, and
It is a high-pressure turbine unit having a vane 26.

The reference numeral 27 designates a fan drive turbine 28 for driving the suction fan 7 of the low pressure compression section 5 by the combustion gas 23, which is provided in the rear of the rear partitioning cylinder 13 adjacent to the high pressure turbine section 24. And stationary vane 29
Is a low-pressure turbine section having.

Reference numeral 30 denotes an afterburner portion formed at a position rearward of the rear partition cylinder 13 inside the engine outer cylinder 3, and the afterburner portion 30 is the rear partition cylinder 13.
A liner 32 that surrounds the rear end of the engine outer cylinder 3 to form a cooling air flow path 31, a fuel injector 33 penetratingly arranged near the rear end of the rear partition cylinder 13, and the rear partition. A mixer 34 formed at the rear end of the cylinder 13 for mixing a part of the air 6 flowing through the bypass passage 10 and the combustion gas 23 from the low-pressure turbine section 27, and the mixer 34. It is constituted by an annular flame stabilizer 35 arranged at the rear.

In the gas turbine engine, the air 6 sucked by the suction fan 7 is compressed by the compression fan 15 and then sent to the combustion chamber 17, where the air 6 is discharged in the combustion chamber 17.
The fuel 20 is injected into and burned, and the combustion gas 23 generated at this time drives the compressor drive turbine 25 and the fan drive turbine 28 to drive the compressor drive turbine 2
5 and the suction fan 7 integrated with the fan drive turbine 28 are provided with a driving force, and the combustion gas 23 exiting the low-pressure turbine section 27 and the bypass passage 10 outside the partition tube body 9 are connected to each other. The flowing air 6 and the mixer 34
The thrust is generated by mixing in the liner 32 of the afterburner section 30 and injecting it from the exhaust nozzle section 4.

Further, by injecting and burning the fuel 20 from the fuel injector 33 penetratingly arranged in the vicinity of the rear end of the rear partition cylinder 13, a larger thrust can be generated.

[0014]

However, the conventional gas turbine engine described above has the following problems.

That is, in the combustion chamber 17, the inflowing air 6
Because of the high flow velocity of, there is a risk that it will always blow out.

In view of the above situation, it is an object of the present invention to provide a gas turbine engine capable of preventing blowout in a combustion chamber.

[0017]

According to the present invention, an annular main combustion liner provided with a fuel injection nozzle is provided in an annular combustion chamber provided inside a gas turbine engine body between the combustion chamber and the main combustion liner. Arranged to form a flow path,
An air flow passage expanded portion is formed in a part of the air flow passage, a sub combustion liner equipped with a fuel injection nozzle is disposed in the air flow passage expanded portion, and an outlet portion of the sub combustion liner is mainly provided. The present invention relates to a gas turbine engine characterized by being connected to a side portion of a combustion liner.

[0018]

The operation of the present invention is as follows.

An air flow passage expansion portion having a large flow passage cross-sectional area is formed in a part of the air flow passage to reduce the flow velocity of air in the air flow passage expansion portion, and the fuel injection nozzle is provided in this air flow passage expansion portion. By disposing the sub-combustion liner provided with, the blow-out in the sub-combustion liner is prevented, and the flame generated in the sub-combustion liner is always kept in the main combustion liner. This prevents blowout in the main combustion liner.

[0020]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows an embodiment of the present invention.

Since the structure other than the combustion chamber 17 is the same as that shown in FIG. 2, FIG. 2 will be referred to when necessary.

An annular main combustion liner 38 as shown in FIG. 1 is disposed inside an annular combustion chamber 17 provided in the engine outer cylinder 3 shown in FIG. The air flow paths 36 and 37 are formed between the combustion chamber 17 and the combustion chamber 17.

Further, in the central partitioning cylinder 12 forming the outer peripheral wall of the combustion chamber 17, several positions in the circumferential direction corresponding to the upstream end of the main combustion liner 38 are projected outward, and the air flow path 37 is formed. An air flow passage enlarged portion 39 is formed in the middle of the air passage, and a sub-combustion liner 40 is disposed inside the air flow passage enlarged portion 39, and the downstream end (outlet portion) of the sub-combustion liner 40 and the main combustion liner A connection liner 41 is used to connect to the intermediate portion of 38.

Inside the upstream ends of the main combustion liner 38 and the auxiliary combustion liner 40, the fuel supply passages 42,
Fuel injection nozzles 44, 45 for injecting the fuel 20 supplied via 43, and vanes 46, 47 for giving a swirling force to the injected fuel 20 are provided.

The main combustion liner 38 and the sub-combustion liner 40 are provided with air introduction holes 48 and 49 for introducing air into their side portions.

Further, in the figure, 50 is a spark plug attached to the auxiliary combustion liner 40, and 51 is an air inlet of the combustion chamber 17.

Next, the operation will be described.

The air 6 compressed in the high-pressure compression section 14 enters the inside of the combustion chamber 17 from the air inlet 51, flows along the main combustion liner 38 in the air flow paths 36 and 37, and is on the side of the main combustion liner 38. The air is introduced into the main combustion liner 38 from an air introduction hole 48 formed in the section.

Further, a part of the air 6 having entered the combustion chamber 17 is guided to the air passage expanding portion 39, and the air passage expanding portion 39.
Along the auxiliary combustion liner 40 provided in the air-intake hole 49 formed in a side portion of the auxiliary-combustion liner 40.
To the inside of the sub-combustion liner 40, the rest flows again in the air flow path 37, and flows into the inside of the main-combustion liner 38 from the air introduction hole 48 formed in the side portion of the main-combustion liner 38.

Then, the fuel 20 is supplied to the fuel injection nozzles 44, 45 through the fuel supply passages 42, 43, and the inside of the main combustion liner 38 is diluted for combustion.
Further, an excessive amount of fuel 20 for combustion is injected into the sub-combustion liner 40, and the spark plug 5
Fuel 2 injected into the auxiliary combustion liner 40 using 0
Ignite 0.

Then, the fuel 2 is discharged inside the auxiliary combustion liner 40.
0 combustion occurs, the generated flame is introduced into the main combustion liner 38 through the connecting liner 41, and the fuel 20 injected into the main combustion liner 38 is ignited by the flame.

Since the auxiliary combustion liner 40 supplies the fuel 20 excessively large for combustion to prevent blowout, the main combustion liner 38 is always generated in the auxiliary combustion liner 40. As a result, the burned-in flame enters, and even if a blowout occurs inside the main combustion liner 38, it is immediately re-ignited, so that the blowout characteristics of the main combustion liner 38 are improved as a whole. It

As a result, combustion can be stably continued inside the main combustion liner 38, and the fuel 20 supplied to the main combustion liner 38 can be diluted.

Further, an air flow passage expanding portion 39 having a partially increased flow passage cross-sectional area is formed in the air flow passage 37 to reduce the flow velocity of the air 6 in the air flow passage expanding portion 39. By disposing the auxiliary combustion liner 40 in the enlarged portion 39, it is possible to more effectively prevent blowout by supplying the excessive combustion fuel 20 to the auxiliary combustion liner 40.

The present invention is not limited to the above-mentioned embodiments, and it goes without saying that various modifications can be made without departing from the scope of the present invention.

[0037]

As described above, according to the gas turbine engine of the present invention, the excellent effect of preventing blowout in the main combustion chamber can be achieved without excessively supplying the fuel.

[Brief description of drawings]

FIG. 1 is a partial enlarged side sectional view of an embodiment of the present invention.

FIG. 2 is an overall schematic side sectional view of a conventional example.

FIG. 3 is a partially enlarged view of FIG.

[Explanation of symbols]

 1 Gas Turbine Engine Main Body 17 Combustion Chamber 36, 37 Air Flow Path 38 Main Combustion Liner 39 Air Flow Path Expanded Part 40 Sub Combustion Liner 44, 45 Fuel Injection Nozzle

Claims (1)

[Claims] 1. An annular main combustion liner having a fuel injection nozzle is arranged in an annular combustion chamber provided inside a gas turbine engine body so that an air flow path is formed between the annular main combustion liner and the combustion chamber. Installed, an air flow passage enlarged portion is formed in a part of the air flow passage, and a sub combustion liner equipped with a fuel injection nozzle is disposed in the air flow passage enlarged portion, and A gas turbine engine having an outlet connected to a side of a main combustion liner.