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TRAILING EDGE PRESSURE AND FLOW REGULATOR FOR GAS TURBINE ENGINE AIRFOILS
TRAILING EDGE PRESSURE AND FLOW REGULATOR FOR GAS TURBINE ENGINE AIRFOILS
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机译：燃气轮机机翼的尾缘压力和流量调节器
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摘要
The present invention relates to a gas turbine engine airfoil (60) comprising an airfoil (84) and a radially spanning trailing edge (102). One internal channel (106) in the airfoil (84) provides a supply pressure (P 1 ) which is received in a second internal channel (126) providing a downstream supply pressure (P 2 ). At least one axial rib (114) separates the second internal channel (126) adjacent to the trailing edge (102) into multiple individual cavities (116). At least one pressure regulating feature (118) is located at an entrance to an individual cavity (116) to control downstream supply pressure (P 2 ) to the trailing edge (102). Exits (110) formed in the trailing edge (102) communicate with an exit pressure (P 3 ). The rib (114) and pressure regulating features (118) cooperate such that the downstream supply pressure (P 2 ) mimics the exit pressure (P 3 ) along the radial span reducing excess cooling flow while securing backflow margin.
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