Gas turbine including external cooling system and method of cooling same
A gas turbine and external cooling technology, which is applied in the direction of gas turbine devices, engine cooling, turbine/propulsion device cooling, etc., can solve problems such as large cooling air consumption, reduced aerodynamic efficiency of compressors and turbines, and complex structural design of central shafts , to achieve the effect of improving the design points and local load performance
Active Publication Date: 2019-05-28
DOOSAN HEAVY IND & CONSTR CO LTD
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Problems solved by technology
[0008] However, in the case of using this method, the flow loss through the internal flow path of the turbine rotor is large, and there is a problem that the cooling air consumption is large for a gas turbine with a high turbine inlet temperature and a high compression ratio.
[0009] In addition, since the diameter of the center hole of the rotor increases, and an additional space where pipes can be inserted is required to separate the cooling air from the space inside the rotor, there is a problem that the structural design of the center shaft and other devices inside the generator becomes complicated.
[0010] This has the consequence of reducing the aerodynamic efficiency of the compressor as well as the turbine
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[0047] Below, refer to the attached Figure 1~5 Preferred embodiments of a gas turbine including an external cooling system and a cooling method thereof according to the present invention will be described.
[0048] In addition, the following terms are defined in consideration of the functions in the present invention, which may be different according to the user's or operator's intention or practice, and the following embodiments are only examples of the structural elements proposed in the claims of the present invention. The matters of illustration do not limit the scope of the claims of the present invention.
[0049] In order to clearly describe the present invention, parts irrelevant to the description are omitted, and the same reference numerals are assigned to the same or similar structural elements throughout the specification. Throughout the specification, when it is mentioned that a certain part "includes" a certain structural element, if there is no contrary descri...
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The invention relates to a gas turbine and a method of cooling the same. A cooling air supply passage of extracting air out of a compressor of the gas turbine and diverting the air to the outside is formed, and vanes and blades of a turbine are cooled by such cooling air supply passage that does not pass through a central shaft of the gas turbine. Consequently, the consumption of cooling air may be reduced, and the flow rate of cooling air may be more easily controlled.
Description
technical field [0001] The present invention relates to a gas turbine including an external cooling system and a cooling method thereof. More specifically, the present invention relates to a cooling air supply flow path that detours to the outside of the gas turbine instead of forming a cooling air supply flow path inside the center shaft of the gas turbine, and static cooling of the turbine. A gas turbine and a method for cooling the vanes and blades are cooled by one cooling air flow path, thereby reducing the amount of cooling air used and freely adjusting the amount of air. Background technique [0002] Generally speaking, as a device that converts the energy of fluids such as water, gas, and steam into mechanical energy, a turbine is usually provided with a plurality of stationary blades or moving blades on the circumference of the rotating body and injects gas to the stationary blades or moving blades. A turbine-like device that rotates at high speed under the action o...
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IPC IPC(8): F02C7/18
CPCF01D5/081F01D5/18F01D9/065F01D25/12F02C7/18F05D2260/14F05D2260/606F01D5/08F02C7/143F02C9/18F01D5/187F01D25/08F02C6/08F02C7/185F05D2260/213F05D2260/232
Inventor 金东和金东权金锺仙赵健焕
Owner DOOSAN HEAVY IND & CONSTR CO LTD