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Power raising method for turboprop aero-engine

An aero engine and engine technology, applied in the direction of engine components, machines/engines, mechanical equipment, etc., can solve the problems of engine improvement that have not been seen in relevant research and reports, and achieve improved plateau starting performance, increased flow capacity, and take-off equivalent power Enhanced effect

Active Publication Date: 2013-08-14
CHINA HANGFA SOUTH IND CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] In order to meet the requirements of a small increase in the take-off equivalent power of the engine, such as a 20% increase, it is necessary to improve the turboprop aero-engine, but there is no relevant research and report on how to improve this type of engine

Method used

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  • Power raising method for turboprop aero-engine
  • Power raising method for turboprop aero-engine
  • Power raising method for turboprop aero-engine

Examples

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Embodiment

[0031] According to a certain type of turboprop aeroengine improved according to the power boosting method of the present invention, under the premise of keeping the engine installation interface, operating speed and adjustment law basically unchanged, the installation angle of the first stage guide vane of the turbine is reduced by 1.5 degrees, The installation angle of the guide vanes of the second stage turbine is reduced by 1 degree, the flow capacity of the turbine is improved, and the aerodynamic stability requirements of the engine are met at the same time.

[0032] Under the requirement that the take-off equivalent power of the engine increases from 3125kW to 3750kW, it is determined that the maximum fuel flow of the turboprop engine increases from 1030kg / h to 1200kg / h, and the gas temperature at the turbine inlet increases from 1065K to 1160K.

[0033] The material of the first-stage guide vane and the second-stage guide vane of the above-mentioned turbine is preferabl...

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Abstract

The invention discloses a power raising method for a turboprop aero-engine with a triple axial-flow turbine, which comprises the following steps of: under the condition of keeping an engine mounting interface, a working speed and an adjustment rule unchanged, determining gas flow of the turbine according to the raised take-off equivalent horsepower; increasing the circulating capacity of the turbine by decreasing installation angles of first-stage guide vanes and second-stage guide vanes; and testing the working aerodynamic stability of the engine and correcting the installation angles of thefirst-stage guide vanes and the second-stage guide vanes according to a test result. According to the power raising method, by changing the installation angles of the guide vanes of the turbine and increasing the maximum gas flow, the take-off equivalent horsepower of the engine is raised slightly, so the highland starting performance of the engine is improved.

Description

technical field [0001] The invention relates to a turboprop aeroengine with a three-stage axial flow reaction turbine, in particular to a method for increasing the power of the engine. Background technique [0002] Turboprop aeroengines with three-stage axial flow reaction turbines are widely used in transport aircraft. [0003] The function of the three-stage axial reaction turbine of the turboprop aero-engine is to convert the thermal energy and pressure potential energy of high-temperature gas into mechanical work, which is used to drive the compressor, propeller and accessories. The gas flows through the channel formed by the annular turbine guide blades and the turbine working blades to realize the expansion and work process of the gas. About 66% of the work produced by the turbine is used to drive the compressor, and the remaining 34% is supplied to the transmission accessories and propeller. [0004] The three-stage axial flow reaction turbine includes the first-sta...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C9/22F01D17/00F01D9/02
Inventor 杨春华王军民
Owner CHINA HANGFA SOUTH IND CO LTD
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