JPS63268938A - Gas turbine engine - Google Patents

Abstract

PURPOSE:To suppress the emission of exhaust NOx through utilizing an optional output from a gas turbine by providing an intake valve on the intake-port side of a combustor for the gas turbine engine, and an exhaust valve on the exhaust-port side thereof respectively, and then providing a means for changing the speed and timing of opening and closing of these intake and exhaust valves. CONSTITUTION:On the intake-port side of a combustor 3 in a gas-turbine engine is provided an intake valve 2 in the rotational structure. While, on the exhaust- port side of the combustor 3 is provided an exhaust valve 4 in the rotational structure. The intake valve 2 and the exhaust valve 3 are subjected to a valve opening-and-closing control in good timing respectively while they are rotating under a rotational speed control through an intake-and-exhaust valve control unit 9. Thereby, the number of explosion per unit time is made independently variable regardless of the rotation of an output shaft, and an optional output can be utilized from a gas turbine. And further, the emission of exhaust NOx can be suppressed to a desired degree.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a gas turbine engine, and in particular, a rotary structure valve is provided at an intake port and an exhaust port of a combustor of a gas turbine engine, respectively, and these intake valves and exhaust valves are connected to each other. This invention relates to a gas turbine engine that enables intermittent explosion of fuel in a combustor while controlling the opening/closing speed and timing of the engine.

[Conventional technology]

Conventionally, turbine engines do not have intake and exhaust valves, so air is continuously compressed by a compressor and sent directly to the combustion chamber, where fuel is injected and continuously burns to rotate the output turbine. ing.

[Problem that the invention seeks to solve]

As described above, in a conventional gas turbine engine, air that is continuously compressed by a compressor is fed into a combustion chamber as it is, and fuel injected into the combustion chamber is continuously combusted.

Continuously compressed air has an outlet called a combustion chamber, and the compression ratio of a centrifugal compressor can only reach about 4 to 6 at most, making it less efficient than a diesel internal combustion engine. The disadvantage is that it is unavoidable.

The object of the present invention is to eliminate the above-mentioned drawbacks and to provide a means for causing fuel to explode and burn at intervals.
In addition to being able to extract any desired output, it also ensures optimum combustion efficiency, including control of NO (nitrogen oxide) components contained in the exhaust gas, as well as high performance at high pressures due to the inertia of compressed air when the exhaust valve is closed. The objective is to provide a gas turbine engine that can be obtained.

[Failure to solve the problem]

The gas turbine engine of the present invention includes an intake valve with a rotating structure provided on the intake port side of the combustor of the gas turbine engine, and an exhaust valve with a rotating structure provided on the exhaust port side of the combustor.
and an intake and exhaust valve control unit that alternately opens and closes the intake valve and exhaust valve with respect to the combustor in a rotating state while corresponding to combustion in the combustor, and controls opening/closing speed and timing. .

〔Example〕

Next, the present invention will be described in detail with reference to the drawings.

FIG. 1 is a side view of one embodiment of the gas turbine engine of the present invention, in which a compressor 1, an intake valve 2, a combustor 3, an exhaust valve 4
, a compressor-driven turbine 7% output turbine 8 and an intake/exhaust valve control section 9, and the combustor 3 is provided with an injector 5 and an igniter 6. Among these components, the intake valve 2 and the exhaust valve 4 have a one-turn structure. In addition, the intake and exhaust valve control section 9 are the parts directly related to the present invention.

The air compressed by the compressor 1 is passed through the intake valve 2 into a combustion chamber having at least one combustion chamber, four combustion chambers in this embodiment.
It is supplied to the combustor 3 of the cylinder. At this time, the exhaust valve 4 is closed, and after the intake valve 2 closes at the next timing, fuel is injected from the injector 5 into the aforementioned closed combustion chamber of the combustion chamber of the combustor 3, and then the igniter 6 ignite it.

Next, when the exhaust valve 4 is opened, the combustion gas becomes a blast and is injected into the compressor drive turbine 7 through the exhaust valve 4 to rotate it, and also passes through the compressor drive turbine 7 to drive the output turbine 8. Rotate.

A compressor drive turbine 7 rotates the compressor 1.

The shaft of the output turbine 8 becomes the output shaft. In Figure 1,
A solid line indicated by an arrow means a connection of axes.

Note that the intake valve 2 and the exhaust valve 4 are controlled to open and close in a well-timed manner while rotating under rotational speed control by the intake and exhaust valve control section 9.

FIG. 2 is a sectional view specifically showing a first embodiment of the intake valve 2, combustor 3, and exhaust valve 4 shown in FIG. Second
Figure (3) shows a sectional view of the intake valve 2, Figure 2 (tb+) shows a sectional view of the combustor 3, and Figure 2 (C) shows a cross-sectional view of the exhaust valve 4. An injector 5 and an igniter 6 are also shown. The intake valve 2 is arranged on the intake side of the combustor 3, and the exhaust valve 4 is connected to the exhaust side of the combustor 3. These intake valves 2 and exhaust valves 4 each have one opening,
Further, the combustor 3 has four openings corresponding to four cylinders.

The intake valve 2 and the exhaust valve 4 have a structure (not shown) that is rotatable about the axis, and each opening has an angle of approximately 90 degrees with respect to the axis. .

FIG. 3 is an explanatory diagram showing the positional relationship between the intake and exhaust valves 2 and 4 and the combustor 3 in the embodiment shown in FIG. The figure shows the intake valve 2, combustor 3, and exhaust valve 4 in order from the top for each of strokes (1) to (8). Line segments on the circumference of the combustor 3 indicate the positions of the four injector 5% igniters 6.

In the stroke (1) of FIG. 3, the combustion chamber A of the combustor 3,
H is in the intake stroke, C and D are in the exhaust stroke. In the stroke (2), the combustion chamber A is completely sealed, and after receiving the injected fuel from the injector 5, it is ignited by the igniter 6Vc and is in the explosion stroke. Combustion chambers B and D are completely in their respective intake and exhaust strokes.

In step (3), exhaust from combustor A and intake of C begin.

In stroke (4), the combustion chamber A is completely in the exhaust stroke, B
C is completely sealed and similarly receives the injected fuel and ignition and is in the explosion stroke, while C is completely in the suction stroke.

In stroke (5), exhaustion of combustion chamber B and intake of combustion chamber D have begun. In stroke (6), the combustion chamber C is completely sealed, and the combustion chamber C is also in the explosion stroke, receiving the injected fuel and ignition.
D is completely on the intake stroke. In the stroke (force), the exhaust of combustion chamber C and the intake of A have begun. In stroke (8), the combustion chamber is completely sealed and is also receiving injected fuel and ignition, and is in the explosion stroke. The combustion chamber A is completely in the suction stroke.Next, the stroke (1) is repeated again, and an explosion is generated in the combustion chambers A-jD, and the blast wave rotates the compressor drive turbine 7° and the output turbine 8.

Figures 2 and 3 show an example of a four-cylinder engine in which the opening of the intake and exhaust valves relative to the combustion chamber occupies approximately 90 degrees with respect to the shaft center. For example, two combustion chambers located at 180 degrees around the axis can be ignited simultaneously, and if the opening is 225 degrees or less, four combustion chambers can be ignited simultaneously.

Similarly, the opening angle θ, which allows the combustion chambers of n cylinders to explode simultaneously, is expressed by the following equation.

n N The stroke of the Kasturbine engine of the present invention is as follows: intake →
Explosion → exhaust → rest (combustion chamber is sealed and ready for intake). Note that N in the above equation is taken into consideration, and in this implementation, N=4.

When repeating the above steps at high speed, the explosion speed will not be in time for the opening of the exhaust port, so it is preferable that the opening angle be less than or equal to the angle determined by the above formula.

The combustion chamber may also be arranged in a thin spiral around the shaft in order to effectively transmit the energy from the explosion to the output turbine.

In FIGS. 2 and 4, the openings of the combustor 3 and the intake and exhaust valves 2 and 4 are provided on the cross section of the shaft, but they may be provided on the circumference as shown in FIG. 5. In this case as well, the aperture angle is determined by the above formula.

In Figure 8g1, no duct is specifically inserted between the compressor 1 and the intake valve 2, but by inserting the duct, the pressure of the compressed air when the intake and exhaust valves 2.4 are closed is reduced due to the inertia of the compressed air. It can be made even stronger.

As mentioned above, the opening and closing speeds of the intake valve 2 and the exhaust valve 4 are determined by their rotational speeds, so these valves are controlled by a servo motor or the like. The intake/exhaust valve control section 9 includes such a servo motor, etc., and controls the opening/closing speed and timing of the valve. As described above, the timing of opening and closing is determined by the opening of the valve and the opening angle and arrangement of the combustion chamber of the combustor 3. The timing of fuel injection and ignition can be easily controlled by detecting the rotational position of the intake and exhaust valves and electronically controlling the injector 5 and igniter 6, and these electronic control circuits are also built into the intake and exhaust valve control section 9.

If the compression pressure is extremely high as in a diesel engine, the igniter 6 may be operated only at startup, and normally ignited by fuel injection.

In this way, the intake valve 2 and the exhaust valve 4 are arranged on the intake side and the exhaust side of the combustor 3, respectively, and the fuel explosion in the combustor 3 is controlled by the intake and exhaust valve control section 9. By controlling the explosions intermittently, continuous explosions can be performed, e.g. 1000
Even if the combustion chamber temperature is around iC, this is 2500 tl.
In a high-temperature state of '2', combustion efficiency can be greatly improved.

〔Effect of the invention〕

As explained above, the present invention provides a gas turbine engine with means for changing the opening/closing speed and timing of the intake and exhaust valves, thereby making it possible to independently vary the number of explosions per unit time regardless of the rotation of the output shaft. , it has the effect of allowing arbitrary output to be extracted. In addition, like conventional turbine engines, the amount of fuel injection can be varied and the output can be varied, so by controlling these two elements it is also possible to perform optimal control to suppress exhaust NOE to the desired degree. effective. Furthermore, since it has intake and exhaust valves, the inertia of the compressed air when the valves are closed has the effect of sealing the combustion chamber at a higher pressure than when the flow is steady, resulting in higher efficiency.

[Brief explanation of drawings]

FIG. 1 is a side view of one embodiment of the gas turbine engine of the present invention, and FIG. 2 specifically shows a first embodiment of the intake valve 2, combustor 3, and exhaust valve 4 of the embodiment of FIG. 3 is an explanatory diagram showing the positional relationship between the intake valve 2.4 of the embodiment shown in FIG. 1 and the combustor 3, and FIG. 3 and an exhaust valve 4 according to a second embodiment, and FIG. 5 is a perspective view specifically showing a third embodiment of the intake valve 2 and combustor 3 of the embodiment shown in FIG. It is. l...Compressor, 2...Intake valve, 3...
...Combustor, 4...Exhaust valve, 5...
・Injector, 6...Igniter, 7...
. . . Compressor drive turbine, 8 . . . Output turbine, 9 . . . Intake and exhaust valve control unit. 1st picture 2 Leap A, F3. C, D -------Ichio keji 3 fig 5 must

Claims (1)

[Claims] In a gas turbine engine, an intake valve having a rotating structure provided on an intake port side of a combustor of the gas turbine engine;
An exhaust valve having a rotating structure provided on the exhaust port side of the combustor, and the intake valve and the exhaust valve are configured to alternately open and close with respect to the combustor in a rotating state while corresponding to the combustion of the combustor, and to adjust the opening/closing speed. 1. A gas turbine engine, comprising: an intake and exhaust valve control section that controls timing.