Turbine blade tip gap reduction system for a turbine engine

Details Turbine blade tip gap reduction system for a turbine engine Turbine blade tip gap reduction system for a turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 11/22 (2006.01)

Patent

CA 2600788

A turbine blade gap control system (10) configured to move a vane carrier (22) and attached ring segments (16) of a turbine engine (18) axially relative to a turbine blade assembly (28) to reduce the gaps (12) between the tips (20) of the turbine blades (14) and the ring segments (16) to increase the efficiency of the turbine engine (18) once operating in a steady state condition. The turbine blade assembly (28) may be formed from a plurality rows (30) of turbine blades (14) extending radially from a rotor (32), wherein each row (30) may be formed from a plurality of turbine blades (14) and wherein the turbine blades (14) may have tips (20) positioned at an acute angle (24) relative to a rotational axis (26) of the turbine blade assembly (28). A vane carrier (22) may be positioned concentric with the rotor (32) and positioned radially outward from the turbine blades (14), and a plurality of ring segments (16) may be attached to the vane carrier (22).

Affiliated with

Also associated with

Rating

Turbine blade tip gap reduction system for a turbine engine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Turbine blade tip gap reduction system for a turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Turbine blade tip gap reduction system for a turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1756385