Industrial Technology Research Institute

Ling-Chia Weng

Wu-Chi Ho

Tzeng-Wuu Wey

Tao-Pang Hsiung

Jia-Ruey Wu

Chia-Yang Chang

Chii-Ron Kuo

Chii-Rong Kuo

Ta-Wei Wang

Hsiao-Wei D Chiang

Ming-Yen Liu

An engine core structure for a gas turbine engine includes an outer annular shaft body, a turbine rotor body, turbine rotor blades radially connected between the outer annular shaft body and the turbine rotor body to hold the turbine rotor body in the rear section of the outer annular shaft body, the outer annular shaft body including slots through which compressed air passes in a radially inward direction, and a can type combustor mounted in a receiving clamber inside the outer annular shaft body to enlarge the diameter of the core shaft, to avoid vibration due to resonance, to save space, to eliminate dissipation of heat, and to improve the thermal efficiency of the gas turbine engine.

Engine core rotor shaft structure for gas turbine engine

A structure of a 50 pound thrust level gas turbine jet engine combustor is a small type 50 pound gas turbine jet engine combustor. The combustor includes a combustor outer liner, a combustor inner liner and a hub. Pressure swirl fuel atomizer and thin film cooling devices are further used. In the combustor, a primary jet flow is matched with a jet tube so as to build a stable recirculation in the primary zone. 12 SIMPLEX fuel atomizers are installed in the inner liner for jetting fuel radially. The fuel must be jetted properly, if it is too close the front plate, the droplet will impact the front plate, then the downstream will possible destroy the recirculation structure. Therefore, if the fuel is jetted in proper positions, then the retaining time of fuel will be reduced greatly and the burning in the primary zone can be enhances. By analyzing and testing, it is appreciated that high temperature will induce at the middle section near the wall of the inner liner. Thus, a one way thin film cooling means and a bidirection thin film cooling means are designed for protecting the liner.

50 pound thrust level turbojet engine

A front plunger pressure-swirl atomizer is disclosed, which is applied to a fuel atomizer of a micro gas turbine engine and includes a nozzle cap, a central plunger swirler, a central plunger fastening barrel. The front plunger pressure-swirl atomizer is installed at the seat of an engine. The present invention has the advantages of occupying a smaller space, only needing a small operating pressure, a simple flow channel structure, and fewer components, being easily assembled and a superior atomizing property. Therefore, the defects, such as complex finishing process of flow channel and difficult to be assembled, in the prior art are improved effectively.

Front pressure-swirl atomizer

A miniture liquid-fueled turbojet engine for powering remote control model aeroplane or light pilotless aircraft includes a plural number of tiny pressure-swirl type atomizers for thoroughly atomizing liquid fuel and a V-gutter flame holder. High combustion efficiency and satisfactory outlet temperature pattern factor can be obtained in the present combustion system of the engine. This is because the system possesses the characteristics such as fine spray of liquid fuel, long residence time of fuel droplets, efficient flame holding mechanism and good mixing in the dilution region. As a result, safety and maneuverability of the present engine can be enhanced in comparison with the engines of prior art.

Miniature liquid-fueled turbojet engine

Growing community of inventors

Chiayi Hsien, Taiwan

Ling-Chia Weng