SU585303A1 - Method of feeding coolant to gas turbine plant blading - Google Patents

Description

The invention relates to gas turbine construction and, in particular, to high-temperature gas turbine installations.

Methods are known for supplying a cooler to a blade apparatus of a gas turbine installation by increasing its flow rate with increasing hour of rotational torque of the turbocharger fl.

However, this method does not ensure the reliability of the installation on start-up modes, characterized by the presence of a climb. gas temperature after turning on the combustion chamber, and the required economy.

Lips are also methods of supplying a cooler to a blade apparatus of a gas turbine installation by adjusting its flow rate when the installation mode changes. Air flow is regulated according to the level of power and temperature of the gases behind the chamber of the open air 2.

However, this method does not provide the necessary efficiency and reliability of the installation at start-up modes.

The purpose of the invention is to improve the efficiency and reliability of the installation on start-up modes.

This is achieved by the fact that at the time of the inclusion of the combustion chamber and. in the period of the subsequent gas temperature reflux, the relative flow rate of the cooler is increased to 1.5-2.0 times its nominal value; after the reflux, the flow rate is reduced to a value of O | 25-O, 3, and maintained unchanged up to limiting, according to the conditions, the strength of the blades of temperature, after which the flow is increased to the nominal value in proportion to the increase in plant capacity.

During the period when the gas temperature is overfilled, the cooler is supplied from an external source, and after it is reflux from the compressor of the installation.

FIG. 1 shows the scheme of the OS; a new installation that implements this method; in fig. Figure 2 shows a graph of the flow rate of the cooler Q on the rotational speed M and the power of the plant, W (where Q is the ratio of the current values of the relative flow rate of the cooler, the frequency of rotation and the power to the nominal).

Gas turbine plant contains compressor 1, chambers / combustion 2 and turbine -3. In order to conserve the air in the circuit, a pipe 4 connected to the compressor 1 is equipped with a refrigerator 4 which through filter 5, the return valve and pipe 7 is connected to the cooling canals in the nozzle 8 of the turbine 3. Air line 7 is connected via a pressure reducing valve 9 to the battery air Bone Y. When the combustion chamber 2 is plugged in, the point Of, see FIG. 2) and in the period of the subsequent reflux of the gas temperature (the ab interval the relative flow rate of the cooler is increased to a value greater than 1.52, 0 times its nominal value. With STO, the reducing valve 9 is opened and the cooler is supplied from the tank 10. After the casting, the flow rate is reduced to the values constituting O are 25–0.3 of the nominal value (interval b-c) and are kept unchanged up to the mode (point 3) of the limiting temperature conditions of the blades. At the same time, the valve 9 is closed, and the flow rate of the cooler is set in accordance with with good abilities The cooling channel of the nozzle apparatus 8. The moment corresponding to point b is characteristic for the beginning of the mixing of the rotary guide vanes of the compressor or its anti-surge valves. The starting point cj of the limit temperature mode (point), the relative flow rate is increased to 1%; the coolant supply method allows to optimize the start-up characteristics of the plant in the direction of lower start-up power, reduction in fuel consumption for start-up, as well as acceleration time to cold the rest of the course (point XX in FIG. 2). Due to the intensive cooling of the nozzle apparatus 8, which prevents its damage when the gas temperature is overloaded, the reliability of the installation on start-up modes is increased. The invention formula 1. Method of supplying a cooler to a blade apparatus of a gas turbine unit by adjusting its flow rate when changing the operating mode of the unit, so that, in order to improve the efficiency and reliability of the unit on start-up modes, at the moment of switching on During the subsequent gas temperature reflux, the combustion chambers increase the relative flow rate of the cooler to 1.5–2.0 times its nominal value; after the reflux, the flow rate is reduced to a value of 0.25–0.3 and vayut unchanged until the limit modes of conditions strength blades evap}, then flow increased to a nominal value in proportion to the power setting. 2. The method according to claim 1, which is otpichayuschih the fact that during the period of the gas temperature reflux, the cooler is supplied from an external source, and after a reflux - from the installation compressor. Sources of information taken into account in the examination. 1. Shvets I. T. et al. Air cooling of parts of gas turbines, Kiev 1974, part G, p. 2O. . 2. US patent No. 3575528, cl. 416-39, 1968. w "5c fftff.f g

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