A double-spoke turbine disk with disk cavity guide ribs
A turbine disk and double-spoke technology, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of low heat exchange efficiency, low pressure at the outlet of the disk cavity, and increased axial stiffness at the center of the disk. To achieve the effect of strengthening heat exchange, increasing flow rate, and improving the ability of axial deformation resistance
Active Publication Date: 2016-07-13
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology
The purpose is to adopt the structure of double-spoke turbine disc and tongue plate with disc cavity guide ribs to solve the problems of low heat exchange efficiency and low pressure at the outlet of the disc cavity of the existing double-spoke turbine disc; several guide ribs and Cooperate with the tongue plate structure and the double-spoke turbine disc to increase the axial stiffness at the center of the disc
Method used
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Embodiment Construction
[0023] This embodiment is a double-spoke turbine disk with a disk cavity guide rib.
[0024] refer to Figure 1-Figure 5 , the double-spoke turbine disc in this embodiment includes a front spoke plate 3, a rear spoke plate 6, a guide rib 2, a tongue plate 10, a front hub 5, a rear hub 9, a cold air channel 1 and a turbine disc on the disc edge. The mortise and groove structure is omitted; the turbine disk edge 4 is evenly distributed with a plurality of disk edge cold air channels 1 along the radial direction of the circumference; 2 is a blade cross-sectional structure, and the bending direction of the guide rib plate 2 is the same as the rotation direction of the turbine disk. In this embodiment, the flow guiding ribs 2 on the front web 3 extend radially toward the edge of the disk in three layers according to the center, and the flow guiding ribs 2 on the rear web 6 extend radially toward the edge of the disk in two layers. , the inclination angle α between the front spoke...
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The invention discloses a double-spoke turbine disc with disc cavity guide ribs. Several guide ribs are arranged on the two spokes of the double-spoke turbine disc. The cold air channel on the edge of the disk is arranged, and the cooling gas enters the cooling blade from the cavity of the double-spoke turbine disk through the cold air channel on the edge of the disk. An annular tongue plate is embedded between the front and rear hubs of the double-spoke turbine disk, and the central channel of the tongue plate communicates with the inner cavity of the turbine disk. The flow guide ribs are distributed in a streamlined layered manner along the rotation direction of the turbine disk, which has a centrifugal supercharging effect during the rotation of the turbine disk, increasing the flow rate and pressure of the cooling air inside the disk cavity; the flow guide ribs increase the heat transfer area , which improves the convective heat transfer efficiency inside the disc cavity, thereby enhancing the heat transfer effect. The tongue plate structure is added at the front and rear hubs of the turbine disc to strengthen the axial stiffness of the center opening; the variable cross-section channel is used at the tongue plate and the disk edge to control the pressure and flow rate of the cooling gas flowing through the channel.
Description
technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a double-spoke turbine disk used on a gas turbine with a disk cavity guide rib and a tongue plate structure for increasing the axial rigidity of the disk center. Background technique [0002] As the turbine inlet temperature of the gas turbine continues to increase, the operating temperature of the high-pressure turbine disk is also getting higher and higher. At present, the temperature of the disk edge of the high-pressure turbine disk is as high as about 700°, and the temperature of the disk center far away from the high-temperature gas is usually about 400°. Traditional high-pressure turbine disks adopt a single-spoke structure. Since this type of turbine disk cannot achieve cooling inside the disk, it is easy to cause uneven temperature and large thermal stress. Generally speaking, the temperature stress of high-pressure turbine disks accounts for roughly Ab...
Claims
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IPC IPC(8): F01D5/06F01D5/08
Inventor 李磊张猛创仝福娟高文静杨未柱杨帆曾小虎岳珠峰苟文选
Owner NORTHWESTERN POLYTECHNICAL UNIV