Patent ID: 8777569

Claim:
A turbine stator vane comprising: a first impingement cavity located in a leading edge region of an airfoil of the vane; a second impingement cavity located in a mid-chord region of the airfoil; a third impingement cavity located in a trailing edge region of the airfoil; a first insert secured within the first impingement cavity; the first insert having impingement cooling holes spaced along a pressure side surface and a leading edge surface that discharge impingement cooling air in a parallel flow path against a pressure side wall and a leading edge wall; the first insert having a sinusoidal shaped piece on a suction side surface with impingement cooling holes that form a series flow of impingement cooling air for a suction side wall of the airfoil; a second insert secured within the second impingement cavity, the second insert having impingement cooling holes spaced along a pressure side surface that discharge impingement cooling air in a parallel flow path against a pressure side wall; the second insert having a sinusoidal shaped piece on the suction side surface with impingement cooling holes that form a series flow of impingement cooling air for the suction side wall of the airfoil; a third insert secured within the third impingement cavity; the third insert having a sinusoidal shaped piece on a suction side surface and a pressure side surface with impingement cooling holes that form a series flow of impingement cooling air for the suction side wall and the pressure side wall of the airfoil; a first row of film cooling holes on the suction side wall of the airfoil and connected to the first impingement cavity downstream from the series flow of impingement cooling air; a second row of film cooling holes connected to the second impingement cavity downstream from the series flow of impingement cooling air; and, a row of exit holes along the trailing edge of the airfoil connected to the third impingement cavity.