A method for debugging the steady-state speed of a turboshaft engine
A technology of turboshaft engine and debugging method, which is applied in the direction of engine components, turbine/propulsion fuel delivery system, fuel control of turbine/propulsion device, etc., can solve problems such as scraping and abrasion, and achieve the effect of reducing test risk
Active Publication Date: 2019-05-31
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0004] At present, there is no literature related to the debugging method of the steady-state speed of the turboshaft engine. In the development stage of the new engine, if there is no scientific speed adjustment method to guide the test and directly increase the speed of the power turbine, it is very likely that scraping
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Embodiment 1
[0032] Such as figure 1 As shown, this embodiment provides a method for debugging the steady-state speed of a turboshaft engine, including the following steps:
[0033] S1. Safe start: Use the gas turbine speed control mode to start the turboshaft engine to the ground idle state, then adjust the hydraulic dynamometer to stabilize the power turbine speed at a rated speed lower than the ground idle state, and avoid the critical speed ;
[0034] Wherein in step S1, if the new machine starts for the first time, the following steps are also included:
[0035] S11. After the speed of the turboshaft engine is stabilized, that is, after the speed of the gas turbine is stabilized at the rated speed of the ground idle state, slowly push up the throttle lever, wherein the maximum acceleration of the gas turbine does not exceed 40r / min / s, so that the gas turbine Turbo speed increased by 10%;
[0036] S12. Then immediately but slowly pull down the throttle lever to adjust the speed of t...
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The invention relates to the field of aero-engines, and discloses a method for regulating the rotating speed of a turboshaft engine in the steady state and application of the method. The method for regulating the rotating speed of the turboshaft engine in the steady state comprises the steps of S1, safe starting, S2, detection of the rotating speed under the condition that the turboshaft engine operates slowly, and S3, running-in in the steady state. According to the method for regulating the rotating speed of the turboshaft engine in the steady state and the application of the method, increasing or decreasing for testing is creatively conducted on a gas turbine and a power turbine in different stages and under different rotating speeds, and thus it is ensured that the gas turbine and thepower turbine can operate safety and reliably under all rotating speeds; and compared with a conventional method that the rotating speed is increased step by step, the method can reduce the risks of scratches, vibration, oil leakage, collisions and the like of a rotor in the engine to a limited extent. The method for regulating the rotating speed of the turboshaft engine in the steady state and the application of the method fill the blank in the field and have important guiding significance.
Description
technical field [0001] The invention relates to the field of aero-engines, and more specifically, to a method for debugging the steady-state rotational speed of a turboshaft engine. Background technique [0002] The complete turboshaft engine adds a power turbine on the basis of a gas generator, wherein the gas generator includes a gas turbine, and the power turbine is behind the gas turbine. Steady-state speed debugging is an important step in the development stage of a new machine, and it is also a prerequisite for performance debugging. During the bench test, the new engine first needs to be run-in to check the engine vibration and the working conditions of various systems, as well as to assess the structural strength and rotor dynamics characteristics of the engine. It can run safely and reliably, thereby reducing the risk of testing. [0003] During the bench test of the turboshaft engine, a hydraulic dynamometer is generally used to connect the output shaft of the po...
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IPC IPC(8): F02C9/28
Inventor 刘渊张鑫张平平
Owner AECC HUNAN AVIATION POWERPLANT RES INST