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INTERNAL COOLING SYSTEM WITH CONVERGING-DIVERGING EXIT SLOTS IN TRAILING EDGE COOLING CHANNEL FOR AN AIRFOIL IN A TURBINE ENGINE
INTERNAL COOLING SYSTEM WITH CONVERGING-DIVERGING EXIT SLOTS IN TRAILING EDGE COOLING CHANNEL FOR AN AIRFOIL IN A TURBINE ENGINE
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机译:汽轮机翼型尾缘冷却通道中带有汇流排出口缝的内部冷却系统
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摘要
An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system (14) at the trailing edge (34) of the airfoil (10) by increasing the contact of cooling fluids with internal surfaces (24, 30) of the pressure and suction sides (36, 38) of the airfoil (10). In at least one embodiment, the trailing edge cooling channel (18) may include one or more converging-diverging exit slots (20) to further pressurize the trailing edge cooling channel (18) and may be formed by a first and second ribs (80, 82) extending between an outer walls (13, 12) forming the pressure and suction sides (36, 38). The converging-diverging exit slot (20) may be formed from a first converging section (84) having an inlet (86) with a larger cross-sectional area than an outlet (88) and is formed from a second diverging section (90) having an inlet (92) with a smaller cross-sectional area than an outlet (94).
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