High-pressure intermediate-stage guide blade of gas compressor for combustion gas turbine
A technology of gas turbines and compressors, which is applied in the direction of machines/engines, liquid fuel engines, components of pumping devices for elastic fluids, etc. It can solve problems such as low work efficiency, affecting the safe operation of compressors, and short service life. It achieves the effect of prolonging the service life, facilitating the axial installation into the wheel groove and increasing the stability
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specific Embodiment approach 1
[0007] Specific implementation mode one: as Figure 1-2 As shown, the high-pressure intermediate guide vane of a gas turbine compressor in this embodiment includes a blade working area 1 and a blade root 2, and the blade working area 1 and blade root 2 are integrated from top to bottom, and the blade working area 1 One side of the blade is the air inlet side 1-1, and the other side of the blade working area 1 is the air outlet side 1-2. The blade working area 1 is a twisted blade with equal cross-section. reduced, there is a relative twist between two adjacent sections, and the blade root 2 is a dovetail-shaped blade root. Designed in this way, this structure enables the blade to be firmly installed into the wheel rim, and is convenient to be axially installed into the wheel groove, with a large bearing area, safety and reliability.
specific Embodiment approach 2
[0008] Specific implementation mode two: as Figure 1-6 As shown, the section height of the blade working area 1 in this embodiment is h, the chord length is b, the installation angle is β, the maximum profile thickness is δ, the total height of the blade working area 1 is L, and the distance from the air outlet edge is The thickness of the air outlet edge at L1 is D1, the height of the blade root 2 is k, and the width of the blade root 2 is W. Other compositions and connections are the same as in the first embodiment.
specific Embodiment approach 3
[0009] Specific implementation mode three: as Figure 1-6 As shown, the section height of the blade working area 1 in this embodiment from the root to the top is h9.50mm-48.50mm, the chord length b is 31.21mm, the installation angle β is 48.67-45.65°, and the maximum thickness δ of the profile line is 1.87mm, the total height L of the blade working area 1 is 39.60mm, the thickness D1 of the air outlet edge at the distance L1 from the air outlet edge is 1mm is 0.39mm, the height k of the blade root 2 is 4.40mm, and the width W of the blade root 2 is 32.50mm. By adopting the above structural parameters, the blades can be easily assembled while ensuring that the outer structure dimensions of the blades meet the design requirements. Other compositions and connections are the same as those in the second embodiment.
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