US 8,998,563 B2 · Active clearance control for gas turbine engine

Abstract

An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance.

Claims15

Dependent claims

An active clearance control system for a gas turbine engine comprising:

a structural member configured to be arranged near a blade tip;
a plenum including first and second walls respectively providing first and second cavities, the first wall including impingement holes, the plenum arranged over the structural member;
and
a fluid source fluidly connected to the second cavity and configured to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member, wherein the first and second walls are concentric C-shaped structures secured to one another to provide the first and second cavities.

1 more element

Dependencies are inferred from the claim text.

Active clearance control for gas turbine engine

Life of this patent

Active clearance control for gas turbine engine

Life of this patent

Abstract

Claims15