A Simple Cycle Gas Turbine Based on Rotating Detonation Combustion

A gas turbine, simple cycle technology, applied in the direction of gas turbine devices, combustion chambers, combustion equipment, etc., can solve the problems of unstable combustion in the detonation combustion chamber, unbearable turbine blades, high outlet temperature of the detonation combustion chamber, etc., to improve the thermal efficiency of the cycle , Improve the working ability and reduce the effect of pollutant discharge

Active Publication Date: 2018-12-21
HARBIN ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among them, the rotary detonation engine is easier to be accepted by the gas turbine due to its advantages of only one ignition and a wider working range. The outlet temperature of the combustion chamber is too high, and the turbine blades cannot withstand

Method used

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  • A Simple Cycle Gas Turbine Based on Rotating Detonation Combustion
  • A Simple Cycle Gas Turbine Based on Rotating Detonation Combustion

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Embodiment Construction

[0021] Exemplary embodiments of the present invention will be described below with reference to the accompanying drawings. In the interest of clarity and conciseness, not all features of an actual implementation are described in this specification. It should be understood, however, that in developing any such practical embodiment, many implementation-specific decisions must be made in order to achieve the developer's specific goals, such as meeting those constraints related to the system and business, and those Restrictions may vary from implementation to implementation. Moreover, it should also be understood that development work, while potentially complex and time-consuming, would at least be a routine undertaking for those skilled in the art having the benefit of this disclosure.

[0022] Here, it should also be noted that, in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the ...

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Abstract

The invention provides a simple cyclical gas turbine based on rotary detonation combustion. The simple cyclical gas turbine based on the rotary detonation combustion comprises a gas compressor, a rotary detonation combustion room, a thermojet priming tube, an ejector, a mixing set, a turbine, a load and a cold source. The rotary detonation combustion room is applied to the simple cyclical gas turbine, and the mixing set is added at the tail part of the combustion room to ensure that working medium at an inlet of the turbine does not overheat. Through utilizing the pressurizing characteristic of the rotary detonation combustion room, the power capability of the working medium at an inlet of the turbine is improved, and under the conditions that the temperature, the efficiency of assembly unit, the pressure ratio of the gas compressor are uniform, the circulation heat efficiency of the gas turbine is improved 5%-10%.

Description

technical field [0001] The invention relates to gas turbine technology, in particular to a simple cycle gas turbine based on rotating detonation combustion. Background technique [0002] The thermal efficiency of the gas turbine cycle is the most important performance index to evaluate the technical level of the gas turbine design. The ways to improve the thermal efficiency of the gas turbine include the following points: increase the initial temperature of the gas and cooperate with the optimal pressure ratio. If the temperature is increased by 10 degrees Celsius, the increase in efficiency will become more and more limited; if the air extraction volume of the compressor is reduced, the compressed air consumed for cooling the turbine blades, cooling the disc and blade root, heat insulation of the case, and balancing the axial force will account for approximately About 20% of the air volume at the inlet of the compressor, if the exhaust air volume at the outlet of the compre...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C3/32F02C3/30F02C7/141F02C7/18F01D25/12F23R3/42
CPCF01D25/12F02C3/305F02C3/32F02C7/141F02C7/18F05D2240/35F23R3/42
Inventor 赵宁波郑洪涛李智明祁磊孟庆洋
Owner HARBIN ENG UNIV
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