A Calculation Method for Pre-Temperature of Gas Turbine Used in Control System
A gas turbine and control system technology, applied in the direction of gas turbine installation, calculation, computer-aided design, etc., can solve the problems of damage to turbine components, affecting the reliability and safety of the whole machine, and cannot accurately reflect the T41 temperature level
Active Publication Date: 2022-04-22
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0005] There is a definite correspondence between the temperature T45 before the power turbine and the temperature T41 before the gas turbine, and T41 can also be indirectly monitored to a certain extent by monitoring T45, but within the full envelope range, T45 cannot accurately reflect the temperature level of T41, and the thermocouple Arranging in the passage of the power turbine will cause aerodynamic loss. If the thermocouple breaks, it will inevitably cause damage to the turbine components, affecting the reliability and safety of the whole machine
The relationship between exhaust gas temperature T5 and T41 is more complicated, and only monitoring T5 is not enough to ensure the safety of gas turbines
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[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0028] refer to Figure 1-2 As shown, the preferred embodiment of the present invention provides a method for calculating the temperature before the gas turbine of the control system, S1: the parameters required for the calculation are measured and collected by the electronic controller, and the parameters include: engine rotor speed Ng (two-rotor engine The above obtained parameters are sent to the control system as the low pressure rotor speed NL), power tur...
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The invention discloses a method for calculating the temperature in front of a gas turbine used in a control system, which relates to the technical field of gas turbines. The parameters required for calculation are measured and collected by an electronic controller, and the obtained parameters are sent to a control system. According to the standard air compressor inlet flow rate function and gas flow function, respectively, to calculate the total power of the power turbine HP 总 and the specific enthalpy of the gas after the power turbine H5, then calculate the specific enthalpy of the gas before the power turbine H45, calculate the temperature T45 before the power turbine, and calculate the standard natural gas turbine temperature T41 from T45 标 , by T41 标 Calculate the temperature T41 before the gas turbine, and determine the temperature correction value T trim , by T trim Calculate the corrected gas turbine front temperature T41 trim , the above functional relationships and correlation coefficients are determined by the engine characteristics, and are written into the electronic controller memory in the form of a data interpolation table. Through the calculation method of the present invention, the control system can obtain accurate gas turbine front temperature.
Description
technical field [0001] The invention relates to the technical field of gas turbines, in particular to a method for calculating the pre-temperature of a gas turbine used in a control system. Background technique [0002] The gas turbine of an aero engine is a key hot-end part of the engine that is subjected to high speed and high temperature, and is a key component that restricts the life of the engine, and the temperature before the gas turbine is a key factor affecting the life of the gas turbine. [0003] A schematic diagram of a typical free-turbine turboprop engine component-level model is shown in figure 2 , in order to monitor and control the temperature before the gas turbine, the engine control system should obtain the T41 temperature (the gas temperature of the 41 section), which is generally measured by a thermocouple. However, since T41 is usually high (greater than 1200°C), conventional thermocouple measurement devices are difficult to withstand. Therefore, in ...
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IPC IPC(8): G06F30/17F02C9/00G06F119/08G06F119/14
CPCG06F30/17F02C9/00G06F2119/08G06F2119/14
Inventor 陈志雄黄波吴志琨罗安阳
Owner AECC HUNAN AVIATION POWERPLANT RES INST