Abstract: An air admission insert particularly adapted for air admission holes in a combustor liner in a gas turbine combustion system comprises a pair of sleeve members, one of which is inserted in the other in axial but eccentric relationship so that the sides of the sleeves contact each other with the intervening space between the sleeves being crescent shaped. The insert is positioned concentrically in a combustor liner air admission hole. Combustion air flows through the insert and into the combustor liner and axially through the crescent space to cool the insert as well as the liner hold perimeter.

Abstract: A plurality of flow channels permit a controlled flow of compressed air to flow therein in contact with the flange of a gas turbine combustor transition piece to reduce the operational temperature of the flange and to thereby reduce stress creep distortion of the flange. The flow channels may be disposed in a surface of the flange facing a seal member or in a surface of the seal member facing the flange. In one embodiment, a longitudinal slot in the flange permits the entry of a sealing flange or seal plate. The flow channels may be disposed in the surface of the slot or in the surface of the flange or seal plate. In another embodiment of the invention, the seal member embraces the exterior of the flange and the flow channels may be disposed in either of the facing surfaces.

Abstract: A covered air scoop for a gas turbine combustor comprising a tubular member radially extending through the combustor shell to define an air inlet. A symmetrical cap member is disposed in spaced, overhanging relationship over the inlet. To enter the combustor, the air must flow into the cap member, thereby causing all air to enter the tube in a substantially uniform manner so that the air flow through all similarly constructed air tubes at a common axial location of the combustor is substantially equal at all times.