Patent ID: 7581923
Filing Date: 2009-09-01
Classification: F01D,Y02T

Abstract:
1. A turbine section for a gas turbine engine comprising: a turbine disk receiving a plurality of rotor blades, said turbine disk being spaced axially from a fixed housing, and a pump/flow guide attached to said fixed housing to guide purge air radially outwardly through a space between said turbine disk and said fixed housing; said fixed housing has a radially inner and radially outer section extending toward said turbine disk, and said radially inner and said radially outer section together forming an intermediate space, with said pump/flow guide having at least a portion extending radially outwardly to at least a radial location of said radially inner section; said rotor blades having a wing extending in a direction toward said radially inner section, and said pump/flow guide providing a flow path from radially inward of said radially inner section into said intermediate space; said pump/flow guide having a forward leg and an aft leg, said forward leg being said portion; said aft leg being provided by a plurality of circumferentially spaced tabs; said circuniferentially spaced tabs having bolt holes to receive a threaded member to secure the flow guide to the housing structure; and passages formed through the forward leg to allow threaded members to be inserted into the bolt holes in the aft leg.