Abstract: A gas turbine engine component has a cooling scheme that utilizes an impingement tube to cool the suction wall and the pressure wall of a mid portion of an airfoil. The impingement tube is formed to not have impingement holes on an end of the impingement tube spaced toward the trailing edge along the suction wall. Impingement holes are formed in the same portion on a side of the impingement tube facing the pressure wall. Pedestals extend from an inner face of the suction wall toward the impingement tube in this area. The use of the pedestals over this area provides greater cooling to a focused area on the suction wall of the airfoil that might otherwise receive inadequate film cooling.

Abstract: A vane for use in a gas turbine engine has a leading edge facing an upstream combustor. The vane has hollow areas that receive an impingement tube for delivering impingement air. The impingement tube includes a radially outer portion and a radially inner portion. An end wall of the radially outer portion is angled relative to a rotational axis of the turbine such that air entering the impingement tube from a radially outer source has dirt directed away from the leading edge. Thus, dirt is less likely to clog leading edge air supply holes. In one embodiment, the inner and outer portions are formed as separate pieces, and in another embodiment, the inner and outer portions are formed as a single piece.

Abstract: A gas turbine engine component has a cooling scheme that utilizes an impingement tube to cool the suction wall and the pressure wall of a mid portion of an airfoil. The impingement tube is formed to not have impingement holes on an end of the impingement tube spaced toward the trailing edge along the suction wall. Impingement holes are formed in the same portion on a side of the impingement tube facing the pressure wall. Pedestals extend from an inner face of the suction wall toward the impingement tube in this area. The use of the pedestals over this area provides greater cooling to a focused area on the suction wall of the airfoil that might otherwise receive inadequate film cooling.

Abstract: A seal for restricting leakage of a fluid from a first chamber, through a gap between two components, to a second chamber, is provided. A slot is formed in each of the two components. The slots face one another and are open to the gap. Each slot contains a longitudinal axis, an upstream surface proximate the first chamber and a downstream surface proximate the second chamber. Disposed in the slots and spanning the gap is a bridging element. The bridging element contains a sectional profile, transverse to the longitudinal slot axis, that includes a flat central portion disposed between two approximately wave shaped end portions. The bridging element spans the gap between the two components with the end portions disposed in the slots, and the central portion disposed in the gap.

Abstract: A turbine airfoil includes an outer wall and a plurality of cooling passages or minicores formed in the outer wall. A web separates each adjacent pair of the minicores. In order to provide more effective, even cooling of the airfoil, a baffle inside the airfoil includes a plurality of outlets aligned with the webs. The fluid outlets direct the cooling fluid directly onto the web. The cooling fluid then flows through the minicores and out through exits in the minicores.

Abstract: An EDM electrode curved in both the the Z and the Y planes permits the formation of film cooling holes in a highly contoured article.

Abstract: An EDM electrode curved in both the the Z and the Y planes permits the formation of film cooling holes in a highly contoured article.

Abstract: A vane for use in a gas turbine engine has a leading edge facing an upstream combustor. The vane has hollow areas that receive an impingement tube for delivering impingement air. The impingement tube includes a radially outer portion and a radially inner portion. An end wall of the radially outer portion is angled relative to a rotational axis of the turbine such that air entering the impingement tube from a radially outer source has dirt directed away from the leading edge. Thus, dirt is less likely to clog leading edge air supply holes. In one embodiment, the inner and outer portions are formed as separate pieces, and in another embodiment, the inner and outer portions are formed as a single piece.