Patent Number: 8,015,817

Title: Cooling structure for gas turbine transition duct

Abstract: A transition duct for conveying hot combustion gas from a combustor to a turbine in a gas turbine engine. The transition duct includes a panel including a middle subpanel, an inner subpanel spaced from an inner side of the middle subpanel to form an inner plenum, and an outer subpanel spaced from an outer side of the middle subpanel to form an outer plenum. The outer subpanel includes a plurality of outer diffusion holes to meter cooling air into the outer plenum. The middle subpanel includes a plurality of effusion holes to allow cooling air to flow from the outer plenum to the inner plenum. The inner subpanel includes a plurality of film holes for passing a flow of cooling air from the inner plenum through the film holes into an axial gas flow path adjacent to the inner side of the inner subpanel.

Inventors: Charron; Richard (West Palm Beach, FL), Snyder; Gary (Jupiter, FL), Landis; Kenneth K. (Tequesta, FL)

Assignee: Siemens Energy, Inc.

International Classification: F02C 1/00 (20060101)

Expiration Date: 2019-09-13 0:00:00