Turbine rear casing support plate outer molded surface modeling design method
A design method and technology of external surface, applied to mechanical equipment, combustion engines, engine components, etc., can solve the problems of large flow loss and difficult processing at the trailing edge
Pending Publication Date: 2022-05-27
AECC SHENYANG ENGINE RES INST
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[0008] The purpose of this application is to provide a method for designing the exterior profile of the rear casing support plate of the turbine, so as to solve the problem that the trailing edge flow loss of the symmetrical support plate in the prior art is relatively large or difficult to process
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[0026] In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
[0027] A method for designing the outer profile shape of a support plate of a turbine rear casing. The outer profile profile design is carried out by adopting "medium arc line + thickness distribution". The leading edge and the trailing edge are respectively in the form of small circles. The center of the circle is the two endpoints of the middle arc. The middle arc is designed with a spline curve. The shape of the spline curve is determined according to the flow direction of the intake and exhaust. When the intake and exhaust are along the axial direction, the middle arc is a straight line. When the air is non-axial, the middle arc is an arc to adapt to diff...
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The invention belongs to the field of axial-flow turbine rear casing support plate profile modeling design, and relates to a turbine rear casing support plate profile modeling design method, which is characterized in that six design parameters, two coefficients and a support plate thickness distribution form are given, and the modeling design of the support plate profile is realized through the correlation design of each parameter; by giving the small circle diameters of the front edge and the tail edge of the supporting plate, the supporting plate can adapt to a wider incoming flow direction, the thickness of the tail edge is guaranteed, the casting requirement is met, and the flow loss of the tail edge is reduced. By giving an angle between a straight line connecting the center of a front edge small circle and the center of a tail edge small circle and a molded surface horizontal line and giving an inlet structure angle and an outlet structure angle of the supporting plate, main airflow in front of and behind the supporting plate of the rear casing can meet the airflow turning requirement of a certain angle, and the flow guiding effect is enhanced; the supporting plate molded surface design is carried out by giving the supporting plate thickness distribution along the mean camber line, the freedom degree of the supporting plate thickness design is higher, and the requirement for the larger thickness of a through pipeline in the supporting plate is met.
Description
technical field [0001] The present application belongs to the field of profile modeling design of axial-flow turbine rear casing support plates, and particularly relates to a design method for the outer profile modeling of a turbine rear casing support plate. Background technique [0002] In the field of aero-engines and gas turbines, low-pressure turbines or power turbines generally use the rear casing structure as the main support point of the engine or gas turbine. A typical rear casing structure diagram is as follows figure 1 . A support plate with a certain thickness is arranged in the flow channel of the rear casing, and its functions are mainly reflected in two aspects: one is the support function, the support plate is supported by itself or supported by the internal force-carrying rod, which is an important force transmission path of the rotor; the second is the internal pipe The function of the road, including the lubricating oil pipeline and the air system bleed p...
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Login to View More IPC IPC(8): F01D25/24F01D25/28
CPCF01D25/24F01D25/28Y02T10/12
Inventor 张兵兵李鑫程瑞罡张勇
Owner AECC SHENYANG ENGINE RES INST