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Oxygen supplementing device for turbine shaft and turboprop engine and working method thereof

A turboprop and engine technology, which is applied to the combustion of gas turbines, machines/engines, and power plants at the intake ports, can solve the problems of reduced engine thrust and reduced engine operating performance, and achieve the effect of eliminating power loss and improving performance.

Inactive Publication Date: 2021-08-03
于力
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  • Claims
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Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide an oxygen supplement device for turboshaft and turboprop engine and its working method in view of the deficiencies in the above-mentioned prior art, so as to solve the problem of the reduction of operating performance and engine thrust reduction of the current two types of engines in plateau areas. It is suitable for the operation of military and civilian turboprop aircraft and turboshaft engine-driven helicopters in high altitude areas

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  • Oxygen supplementing device for turbine shaft and turboprop engine and working method thereof
  • Oxygen supplementing device for turbine shaft and turboprop engine and working method thereof
  • Oxygen supplementing device for turbine shaft and turboprop engine and working method thereof

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Embodiment Construction

[0038] 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 some of the embodiments of the present invention, but not all of them. 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.

[0039] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientation or positional relationship indicated by "vertical", "horizontal", "top", "bottom", "inner", "outer", "side", "end", "side" etc. is based on the Orientation or positional relationship is only for the convenience of describing the present invention and simplif...

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Abstract

The invention discloses an oxygen supplementing device for a turbine shaft and a turboprop engine and a working method thereof. An injection device is arranged at an air inlet of the engine and connected with an oxygen supplementing cabin through an oxygen conveying pipe; and the injection device can inject mixed gas of oxygen generated by the oxygen supplementing cabin and water vapor into an air inlet channel of the engine. The invention is suitable for the operation of military and civilian turboprop aircrafts and helicopters driven by turboshaft engines in high altitude areas.

Description

technical field [0001] The invention belongs to the technical field of aircraft power engineering, and in particular relates to an oxygen replenishing device for a turbine shaft and a turboprop engine and a working method thereof. Background technique [0002] In recent years, limited by the thin air, helicopters and transport aircraft in high-altitude areas need to reduce their load. Helicopters and transport aircraft that have not been modified with enhanced power cannot even fly in plateau areas, resulting in loss of transport capacity and waste of resources. Therefore, there is an urgent need to improve the power performance of the engine at high altitudes. [0003] The air at high altitudes is thin and has low oxygen content. The air inhaled into the engine cannot completely burn the fuel, and the reduction in combustion efficiency leads to a sharp decline in engine performance and a significant reduction in thrust. If the engine can be artificially supplemented with o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/057B64D33/02
CPCF02C7/057B64D33/02
Inventor 于力于翔刘静
Owner 于力
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