Rotor blade for heavy duty fuel gas turbine engine with medium and low heat values
A technology of rotor blades and gas turbines, applied in the direction of machines/engines, engine components, blade support components, etc., can solve problems such as thermal fatigue, blade tip oxidation, creep damage, etc., to reduce thermal stress, inhibit oxidation, prolong The effect of service life
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specific Embodiment approach 1
[0022] Specific implementation mode one: combine Figure 1 to Figure 4 Describe this embodiment, this embodiment includes a rotor blade body 10, the rotor blade body 10 includes a blade tip 14, a tenon portion 11, a blade body 13 and a platform portion 12, the tenon portion 11 is tenoned on the platform portion 12, and the blade body 13 And the blade tip 14 is installed on the platform portion 12; the blade body 13 includes a suction side 21, a pressure side 22, a front edge 23, a cold air guide groove 30, an upper end wall 31 on the suction side, an upper end wall 32 on the pressure side, and a first cover plate 41 and the second cover plate 42, the suction side 21 and the pressure side 22 are connected to each other at the axial leading edge by the leading edge 23 so as to define a serpentine cooling passage 15 inside the airfoil, and the suction side 21 and the pressure side 22 are connected at the trailing edge A U-shaped slit 34 is formed at the position, and the U-shaped...
specific Embodiment approach 2
[0023] Specific implementation mode two: combination Figure 1 to Figure 3 Describe this embodiment. In this embodiment, the upper end wall 31 on the suction side radially stretches a first distance 35 from the end face of the cold air guide groove 30 on the blade tip, and the upper end wall 32 on the pressure side radially stretches from the end face of the cold air guide groove 30 on the blade tip. The second distance is 36. In this way, if there is friction between the rotor blade tip 14 and the stator guard ring, only the upper end wall 31 on the suction side and the upper end wall 32 on the pressure side are in contact with the guard ring, which helps to reduce the friction on the end face of the cold air guide groove 30 and avoid the first The cooling openings 53 of the cover plate 41 and the second cover plate 42 are blocked. Other compositions and connections are the same as in the first embodiment.
specific Embodiment approach 3
[0024] Specific implementation mode three: combination Figure 1 to Figure 3 The present embodiment will be described. In this embodiment, the first distance 35 and the second distance 36 have the same height at the same axial position. Therefore, the suction-side upper end wall 31 is coplanar with the pressure-side upper end wall 32 . Such setting, because the working temperature of the leading edge of the blade tip 14 is lower than that of the trailing edge of the blade tip 14, the trailing edge needs more cooling gas, and the first distance 35 and the second distance 36 are equal in height to ensure that the cooling gas cools along the tip of the blade. The flow guide slots 30 flow toward the trailing edge to provide additional convective cooling to the trailing edge, further reducing the thermal load on the tip trailing edge. Other compositions and connections are the same as those in the second embodiment.
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