JP2010242672A - Fuel supply device for gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a fuel supply device for a gas turbine which prevents the generating distribution to the combustion in the combustion chamber at the ignition, as well as, the fuel from flowing-in the engine at the ignition error or before the ignition when the fuel nozzles are of a pressure spray type. <P>SOLUTION: When the pressure in the fuel manifold 2, which is a fuel pipe in which the fuel is supplied and the fuel flows, reaches to the prescribed value, it is constituted that multiple is connected to this fuel manifold 2 to communicate the fuel nozzles 4 for supplying the fuel to the combustion chamber 1 with the fuel manifold 2 through the on-off valve 5, and the prescribed value is set to the pressure where the fuel is charged in the fuel manifold 2, whereby the fuel is evenly supplied from every fuel nozzles 4 to the combustion chamber 1 without any bias to prevent the generation distribution to the combustion in the combustion chamber 1 at the ignition, as well as, to prevent the fuel from flowing-in the engine at the ignition error or before the ignition, when the fuel nozzles 4 are a pressure spray type. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a fuel supply device for a gas turbine.

  Conventionally, a gas turbine that compresses the atmosphere with a compressor, burns the compressed air in a combustion chamber, rotates the turbine with combustion gas from the combustion chamber to obtain mechanical power, and obtains thrust from high-speed exhaust gas It has been known. The gas turbine includes a fuel supply device that supplies fuel to the combustion chamber to burn compressed air in the combustion chamber. The fuel supply device is a fuel pipe through which fuel is supplied and the fuel flows. A fuel manifold is arranged in an annular shape so as to surround the combustion chamber, and a plurality of fuel nozzles are arranged on the fuel manifold so as to face inward along the circumferential direction, and combustion is performed from these fuel nozzles. It is known that compressed air is combusted in the combustion chamber by injecting fuel into the chamber (see, for example, Patent Document 1).

JP-A-11-223340

  However, in the gas turbine fuel supply apparatus, the fuel injected from the fuel nozzles of the fuel manifold into the combustion chamber is biased, and the combustion can be distributed during ignition in the combustion chamber (when the engine is started). There is a problem that it ends up.

  In particular, when the fuel nozzle is a pressure spray type, the fuel does not atomize if the fuel pressure (fuel pressure) is below a specified value, so that the fuel flows into the engine before an ignition mistake or ignition. There is also a problem.

  The present invention has been made to solve such problems, and can prevent the distribution of combustion from occurring during ignition in the combustion chamber (engine start), and the fuel nozzle is of the pressure spray type. It is an object of the present invention to provide a fuel supply device for a gas turbine that can prevent an ignition error or a fuel from flowing into an engine before ignition.

  A fuel supply apparatus for a gas turbine according to the present invention is a fuel supply apparatus used in a gas turbine that generates a combustion gas by supplying fuel to a combustion chamber to generate a combustion gas, and rotates the turbine by the combustion gas. A fuel supply for a gas turbine comprising: a fuel manifold that is a fuel pipe through which fuel is supplied and through which the fuel flows; and a fuel nozzle that is connected to the fuel manifold and supplies fuel to the combustion chamber When the pressure in the fuel manifold reaches a specified value, the apparatus includes an on-off valve that communicates the fuel nozzle and the fuel manifold.

  According to the present invention as described above, when the pressure in the fuel manifold, which is a fuel pipe through which fuel is supplied and the fuel flows, reaches a specified value, a plurality of fuel manifolds are connected to the fuel manifold and the fuel is connected to the combustion chamber. A fuel nozzle for supply and the fuel manifold communicate with each other by an on-off valve. For this reason, by setting the specified value to the pressure when the fuel manifold is filled with fuel (the pressure when the fuel manifold is filled), the fuel is evenly supplied from each fuel nozzle to the combustion chamber without any bias. In addition, it is possible to prevent the combustion from being distributed during ignition, and to prevent the fuel from flowing into the engine before ignition or ignition when the fuel nozzle is a pressure spray type.

  As described above, according to the present invention, it is possible to prevent the distribution of combustion from occurring at the time of ignition in the combustion chamber, and when the fuel nozzle is a pressure spray type, the fuel flows into the engine before the ignition error or ignition. It is possible to provide a gas turbine fuel supply device that can prevent this.

1 is a schematic configuration plan view showing a fuel supply device for a gas turbine according to an embodiment of the present invention. FIG. 2 is a cross-sectional configuration diagram specifically showing an arrangement structure of a fuel nozzle and an on-off valve in FIG. 1 and showing a fuel nozzle / on-off valve separation type in which the fuel nozzle and the on-off valve are separated. FIG. 3 is a cross-sectional configuration diagram specifically showing another arrangement structure of the fuel nozzle and the on-off valve in FIG. 1 and showing a fuel nozzle / on-off valve integrated type in which the fuel nozzle and the on-off valve are integrated.

  A preferred embodiment of a gas turbine fuel supply apparatus according to the present invention will be described below with reference to FIGS. In each figure, the same symbol is attached to the same element, and duplicate explanation is omitted.

  FIG. 1 is a schematic plan view showing a fuel supply device for a gas turbine according to an embodiment of the present invention, and FIGS. 2 and 3 specifically show the arrangement structure of a fuel nozzle and an on-off valve in FIG. It is each cross-sectional block diagram, and the fuel supply device of this embodiment generates combustion gas by burning compressed air (working gas) from a compressor with a gas turbine, specifically, fuel supplied to a combustion chamber. And it is used for the gas turbine which rotates a turbine with the said combustion gas.

  As shown in FIG. 1, a fuel supply device 100 for a gas turbine supplies fuel to a combustion chamber 1. A fuel manifold 2 serving as a fuel pipe and fuel from the fuel manifold 2 to the combustion chamber 1 are provided. And a plurality of fuel nozzles 4 for injection and supply.

  The fuel manifold 2 is configured by arranging pipes extending in a semi-circular shape facing each other so as to form a circle along the peripheral surface of the combustion chamber 1, and each base end is for supplying fuel. Connected to the actuator 3.

  A plurality of fuel nozzles 4 are arranged along the fuel manifold 2 and connected to the fuel manifold 2 so as to face the inner combustion chamber 1. Here, nine fuel nozzles 4 are connected to the fuel manifold 2 on one side forming a substantially semicircle.

  Here, particularly in the present embodiment, an on-off valve 5 is provided between the fuel manifold 2 and the fuel nozzle 4.

  The on-off valve 5 is opened when the pressure reaches a specified value, and communicates between the fuel manifold 2 and the fuel nozzle 4. The specified value is a pressure when the fuel is filled in the fuel manifold 2. (Pressure when full) is set.

  Here, even if the fuel nozzle 4 and the on-off valve 5 are a fuel nozzle / on-off valve separation type in which the fuel nozzle 4 and the on-off valve 5 are separated as shown in FIG. 2, as shown in FIG. A fuel nozzle / open / close valve integrated type in which 4 and the open / close valve 5 are integrated may be used.

  Here, as shown in FIG. 1, the on-off valve 5 is not provided for the fuel nozzle 4 at the end of the fuel manifold 2, and the fuel manifold 2 and the fuel nozzle 4 at the end are in communication with each other. ing.

  Next, the operation of the fuel supply apparatus 100 for a gas turbine configured as described above will be described.

  Before the engine is started, the pressure in the fuel manifold 2 is lower than the specified value described above, and therefore the on-off valve 5 is closed.

  In this state, when fuel is supplied from the actuator 3 into the fuel manifold 2, the fuel flows from the base end to the end in the fuel manifold 2, and when reaching the end in the fuel manifold 2, the fuel enters the fuel manifold 2. The fuel is filled, and the pressure in the fuel manifold 2 reaches a specified value.

  At this time, fuel is injected from the fuel nozzle 4 at the end of the fuel manifold 2, and at the same time, since the pressure in the fuel manifold 2 has reached a specified value, the on-off valve 5 is opened from the closed state. Fuel is also injected from the fuel nozzles 4 other than the terminal fuel nozzle 4 at the same time.

  Therefore, the fuel is uniformly injected and supplied from each fuel nozzle 4 to the combustion chamber 1 without unevenness. As a result, it is possible to prevent the distribution of combustion from occurring when the combustion chamber 1 is ignited (when the engine is started).

  Further, as described above, when the pressure in the fuel manifold 2 reaches a specified value, the on-off valve 5 is opened from the closed state. Therefore, when the fuel nozzle 4 is a pressure spray type, the fuel is always atomized, and an ignition error or The fuel is prevented from flowing into the engine before ignition, and when the engine is stopped, the pressure in the fuel manifold 2 is lower than a specified value and the on-off valve 5 is closed, so that the fuel in the fuel manifold 2 is closed. Is prevented from flowing into the combustion chamber 1.

  The present invention has been specifically described above based on the embodiment. However, the present invention is not limited to the above embodiment. For example, in the above embodiment, the number of parts is reduced and the cost is reduced. The on-off valve 5 is not provided for the fuel nozzle 4 at the end of the fuel manifold 2, but may be provided as a matter of course.

  DESCRIPTION OF SYMBOLS 1 ... Combustion chamber, 2 ... Fuel manifold, 4 ... Fuel nozzle, 5 ... On-off valve, 100 ... Fuel supply apparatus of gas turbine.

Claims (1)

A fuel supply device for use in a gas turbine that generates a combustion gas by supplying fuel to a combustion chamber to generate a combustion gas, and rotates the turbine with the combustion gas. In a fuel supply apparatus for a gas turbine, comprising: a fuel manifold that is a flowing fuel pipe; and a fuel nozzle that is connected to the fuel manifold and supplies the fuel to the combustion chamber.
A fuel supply apparatus for a gas turbine, comprising: an on-off valve that communicates the fuel nozzle and the fuel manifold when the pressure in the fuel manifold reaches a specified value.

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