Thermal insulating structure
A heat shield and combined technology, applied in the direction of blade support components, jet propulsion devices, engine components, etc., can solve the problem that the roots of turbine blades cannot be cooled, affect the service life of turbine blades, and have large radiation and conduction heat transfer, etc. Problems, achieve the effect of reducing radiation, obvious heat insulation effect, and reducing heat conduction
Active Publication Date: 2014-08-27
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology
Even so, the heat insulation effect of the existing heat insulation measures is still very unsatisfactory in the actual operation of the gas turbine. The radiation and conduction heat transfer of the high temperature gas to the rotor bearing and other parts is still relatively large, and the roots of the turbine blades cannot be effectively heated. cooling, the temperature is also very high, which greatly affects the service life of the turbine blades
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[0020] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.
[0021] Such as Figures 1 to 5 As shown, the heat insulation structure of the present invention is used to insulate the shafting parts of the gas turbine, including a heat insulation plate 1 and a mounting ring 2, the compressor axial diffuser outlet 8 of the gas turbine, the gas volute 3, The rotor casings are all arranged in the gas collecting casing 4, and the gas collecting casing 4 is filled with the compressed air 5 discharged from the axial diffuser outlet 8 of the compressor. The gas volute 3 contains the high-temperature gas from the combustion chamber, the outlet of the gas volute 3 is connected to the inlet of the turbine guide 6, and the heat insulation structural components are located in the space between the gas volute 3 and the rotor cas...
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The invention discloses a thermal insulating structure of a gas turbine shaft system part. The thermal insulating structure comprises a thermal insulating plate and an installing ring, wherein the thermal insulating plate is welded with the installing ring so as to form a thermal insulating structure component; and the component is connected with a turbine guider through the installing ring in an interference fit manner. The structure is simple in mode, convenient to machine and low in cost, radiation and heat conduction of high-temperature fuel gas to parts such as a rotor bearing are effectively reduced; and meanwhile a turbine vane root is cooled down, so that the vane is protected and the heat conduction of the turbine vane to the center of a turbine disc is reduced.
Description
technical field [0001] The invention belongs to the overall structure of a gas turbine or an aero-engine, and the field of thermal insulation structure design of shaft parts. Specifically, it refers to a structural form used in the heat insulation structure of gas turbine or aero-engine shafting parts. Background technique [0002] There are many general structures of gas turbines or aero-engines in the prior art. In the general structure of some gas turbines or aero-engines, the compressed air and the gas volute coexist in a gas-collecting casing, so that the shafting parts, such as rotor bearings, are in the In the high temperature environment of compressed air (gas). It is necessary to set up a thermal insulation structure to reduce the thermal load of the shafting parts. A common heat insulation measure is to wrap a heat insulating material filling layer on the outside of the shafting parts to prevent heat from being transferred to the center of the shafting. Even so,...
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IPC IPC(8): F02C7/24F01D25/08F01D5/18
Inventor 陈巍
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI