Gas turbine engine sealing device
A gas turbine and engine technology, applied in engine components, machines/engines, mechanical equipment, etc., to achieve the effect of strong stability and good sealing effect
Active Publication Date: 2018-10-09
AECC SHENYANG ENGINE RES INST
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Problems solved by technology
[0003] The object of the present invention is to provide a gas turbine engine sealing device to at least solve the problem of the stability of the existing sealing device
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[0016] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. 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. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention relates to the field of aircraft engine design, in particular to a gas turbine engine sealing device. The stability problem of an existing sealing device is at least solved. The gas turbine engine sealing device comprises annular comb teeth, an annular mounting base and annular-plate-shaped sealing rings. The number of the annular-plate-shaped sealing rings is the same as that of the comb teeth; the sealing rings and the comb teeth are coaxially and fixedly arranged on the inner ring face of the mounting base; the sealing rings and the comb teeth are distributed in the axial direction at intervals; and the inner diameter of the sealing rings is smaller than the outer diameter of the comb teeth. Each sealing ring comprises a plurality of sector flake-like sealing pieces; each sealing piece is made of elastic metal materials, and the central angles of the sealing pieces are smaller than 180 degrees; and multiple sealing pieces are sequentially arranged to form one complete sealing ring in the circumferential direction. According to the gas turbine engine sealing device, the sealing rings can abut against the corresponding comb teeth under the gas flow effect to form sealing connection, so that a sealing effect is achieved; and the gas turbine engine sealing device can adapt to variation of temperatures and pressure under different states of an engine, and has good sealing effects and high stability.
Description
technical field [0001] The invention relates to the field of aeroengine design, in particular to a sealing device for a gas turbine engine. Background technique [0002] In order to meet different functional requirements inside the gas turbine engine, many chambers with different pressures need to be established. In order to ensure the relative independence between the various chambers, a sealing device must be provided between the chambers. In existing gas turbine engines, the types of sealing devices are mainly toothed honeycomb structures and brush-type sealing structures; figure 1 As shown, it is a grate tooth honeycomb structure, including ring-shaped grate tooth 1, honeycomb structure 2 and mounting seat 3, and the honeycomb structure 2 is installed through the mounting seat 3; however, in the above grating tooth honeycomb structure, the honeycomb structure 2 is radially The direction is basically fixed, that is, the distance between the honeycomb structure 2 and the...
Claims
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IPC IPC(8): F01D11/00
CPCF01D11/003
Inventor 曹阳
Owner AECC SHENYANG ENGINE RES INST