Blade of gas turbine
A gas turbine and blade technology, which is applied to the supporting elements of blades, mechanical equipment, engine elements, etc., can solve the problems of using large amount of cold air, reducing the use efficiency of the whole machine, and poor heat exchange effect, so as to increase the heat exchange area and improve the Cooling efficiency, the effect of improving the use efficiency
Pending Publication Date: 2019-09-17
CHINA UNITED GAS TURBINE TECH CO LTD
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Problems solved by technology
[0003] However, the cooling method of the blades of the gas turbine in the prior art has the problems of poor heat exchange effect, low cooling efficiency and large amount of cold air used, which reduces the use efficiency of the whole machine
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Embodiment Construction
[0023] Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.
[0024] Such as Figure 1-4 As shown, the blade of the gas turbine according to the embodiment of the present invention includes a blade body 1 and an impingement sleeve 2 . There is a cooling channel 3 inside the blade body 1, and a plurality of air film holes 4 are arranged on the blade body 1. The air film holes 4 communicate with the cooling channel 3, and the cooling air flow in the cooling channel 3 is ejected through the air film holes 4 and is injected into the main flow of gas outside. Attached to the outer surface of the blade body 1 under pressure, so as to realize the cooling of the outer surface of the blade body 1, a plurality of spoilers 5 are arra...
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The invention discloses a blade of a gas turbine. The blade of the gas turbine comprises a blade body and an impact sleeve; a cooling channel is formed in the blade body, a plurality of air film holes communicating with the cooling channel are formed in the blade body, a plurality of turbulent flow pieces are arranged on the wall of the cooling channel, each turbulent flow piece comprises a first turbulent flow rib and a second turbulent flow rib, and the first turbulence ribs and the second turbulence ribs are crossed with each other; and the impact sleeve is arranged in the cooling channel, an annular channel is formed between the impact sleeve and the wall of the cooling channel, an internal cooling space is defined by the impact sleeve, and a plurality of impact holes communicating with the annular channel and the internal cooling space are formed in the impact sleeve. According to the blade of the gas turbine, the heat exchange area is increased, the cooling efficiency is improved, and the use efficiency of the whole machine is improved.
Description
technical field [0001] The invention relates to the technical field of gas turbines, in particular to a blade of a gas turbine. Background technique [0002] The blade of the gas turbine is one of the key components in the turbine of the gas turbine, which is used to convert the thermal energy of the gas into the mechanical work of the turbine. Therefore, the structure of the gas turbine blade will affect the performance of the turbine and even the whole gas turbine. The blades of gas turbines are usually directly exposed to high heat load environments, especially the heat load on the blade body and top of the blades increases significantly, resulting in easy oxidation and creep damage of the blades. Therefore, in order to ensure the normal and reliable operation of the blades, effective cooling of the blades is required. [0003] However, the cooling method of the blades of the gas turbine in the prior art has the problems of poor heat exchange effect, low cooling efficie...
Claims
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IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/188
Inventor 田一土石殷宇阳李成李骁刘欢高维彤翟芳芳曲观书
Owner CHINA UNITED GAS TURBINE TECH CO LTD