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Realizing method for efficient gas turbine

A technology for gas turbines and implementation methods, applied in the direction of gas turbine devices, engine cooling, turbine/propulsion device cooling, etc., can solve the problems of limiting engine efficiency and power, difficulty in heat dissipation of turbine blades, and increase, so as to improve efficiency and power , Increase the temperature, easy to dissipate heat

Inactive Publication Date: 2007-01-03
李志文
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The main disadvantage of existing gas turbines is that the heat dissipation of the turbine blades is difficult, which limits the efficiency and power of the engine.

Method used

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  • Realizing method for efficient gas turbine
  • Realizing method for efficient gas turbine
  • Realizing method for efficient gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0011] Moving blade 2 and moving blade 6 are arranged on the shell 9, and this whole structure and its function are equivalent to the structure and its function that the compressor rotor of existing gas turbine engine, turbine rotor and turbine shaft are formed; 5 is arranged on the inner casing 1, and the whole structure and its functions are equivalent to the structure and functions of the existing gas turbine engine compressor stator, turbine stator and outer shell; the inner casing 1 is also provided with a spark plug (not shown in the figure) out) and fuel nozzle 4, the fuel nozzle 4 is provided with swirler (not shown in the figure), can refer to figure 1 . When the engine is working, the gas generated in the combustion chamber drives the moving blade 6 and then drives the casing 9 to drive the moving blade 2 to rotate around the axis together. The moving blade 2 sucks in air from the outside, and the air enters the combustion chamber to mix and burn with fuel, and the g...

Embodiment 2

[0013] Such as figure 2 As shown, on the basis of Embodiment 1, the part of the inner shell 1 passing through the combustion chamber is removed, so that the space of the combustion chamber is greatly increased, the flow velocity of the air flowing through the combustion chamber can be greatly reduced, and the fuel can be burned more stably. . Also can increase several fuel nozzles 4 this moment, promptly increase fuel injection quantity, thereby can greatly increase the power of engine.

Embodiment 3

[0015] On the basis of Embodiment 1 or Embodiment 2, the moving blade 2 used in the present invention may be an axial flow blade or a centrifugal blade. And the moving blade 6 can be a traditional turbine blade or a blade of other forms, such as a blade with a cavity inside, and one end (blade root end) of the cavity communicates with the atmosphere. When the present invention uses this blade, its outside structured as image 3 shown. The high-temperature gas passes through the passage 7, while the external cold air passes through the cavity 8. The structure and function between two adjacent passages 7 are equivalent to traditional turbine blades. Please refer to Figure 4 . As a result, the rotor blade 6 can be cooled better.

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Abstract

The present invention relates to a method for implementing high-efficiency gas turbine. It is characterized by that two movable blades are set on the external shell, said whole structure and its function are identical to the structure composed of air compressor rotor, turbine rotor and turbine shaft of existent gas turbine engine and its function; and two static blades are set on the internal shell, said structure and its function are identical to the structure composed of air compressor stator, turbine stator and external shell of existent gas turbine engine and its function. Besides, said invention also provides the concrete working principle of said high-efficiency gas turbine and its operation method.

Description

Technical field: [0001] The invention relates to a gas turbine, in particular to a gas turbine in which the outer shell rotates around the axis and the inner shell is stationary. Background technique: [0002] The main disadvantage of the existing gas turbines is that the heat dissipation of the turbine blades is difficult, which limits the increase of the efficiency and power of the engine. Invention content: [0003] The invention provides a method for realizing a high-efficiency gas turbine, which can improve the deficiencies in the background technology. [0004] The realization method of the present invention is: moving blade 2 and moving blade 6 are arranged on the casing 9 (outer wall), and the whole structure is used as a rotor; on the inner casing 1 (inner wall), stationary blade 3 and stationary blade 5 are arranged (also can not be provided with stationary blade 5), the inner shell 1 is stationary. The gas produced in the combustion chamber drives the entire r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/12F01D5/18F02C3/04
Inventor 李志文
Owner 李志文