Rotor thrust balance activated tip clearance control system
First Claim
Patent Images
1. A gas turbine engine with a blade tip clearance control, the engine comprising:
- a rotor shaft extending along an axis of the engine;
a turbine rotor disc having a plurality of turbine rotor blades extending therefrom;
a turbine blade tip shroud forming a blade tip gap with the plurality of turbine rotor blades;
a compressor rotor disc having a plurality of compressor blades extending therefrom;
a rotor shaft bias means to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance increases;
a pressure force developed from the engine operation and acting on the compressor and turbine rotor discs to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance decreases;
the rotor shaft is a horizontal aligned rotor shaft; and
,the rotor shaft bias means is a compression spring.
4 Assignments
0 Petitions
Accused Products
Abstract
A gas turbine engine with a rotor shaft that is moveable in an axial direction so change a blade tip clearance, where the rotor is displaced by a spring to increase the blade tip clearance and is displaced by a pressure created by the compressor and turbine during engine operation that will close the blade tip clearance. This is especially useful during engine shutdown to prevent blade tip rubbing against the stationary shrouds.
-
Citations
9 Claims
-
1. A gas turbine engine with a blade tip clearance control, the engine comprising:
-
a rotor shaft extending along an axis of the engine; a turbine rotor disc having a plurality of turbine rotor blades extending therefrom; a turbine blade tip shroud forming a blade tip gap with the plurality of turbine rotor blades; a compressor rotor disc having a plurality of compressor blades extending therefrom; a rotor shaft bias means to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance increases; a pressure force developed from the engine operation and acting on the compressor and turbine rotor discs to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance decreases; the rotor shaft is a horizontal aligned rotor shaft; and
,the rotor shaft bias means is a compression spring. - View Dependent Claims (2, 3, 4)
-
-
5. A gas turbine engine with a blade tip clearance control, the engine comprising:
-
a rotor shaft extending along an axis of the engine; a turbine rotor disc having a plurality of turbine rotor blades extending therefrom; a turbine blade tip shroud forming a blade tip gap with the plurality of turbine rotor blades; a compressor rotor disc having a plurality of compressor blades extending therefrom; a rotor shaft bias means to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance increases; a pressure force developed from the engine operation and acting on the compressor and turbine rotor discs to bias the rotor shaft in a direction such that the turbine rotor blade tip clearance decreases; the rotor shaft is a vertical aligned rotor shaft; the rotor shaft bias means is the weight of the rotor shaft; and
,a counter weight spring to bias the vertical aligned rotor shaft against the weight of the rotor shaft.
-
-
6. A process for controlling a blade tip clearance in a turbine of a gas turbine engine, the blade tips and a stator housing formed at an angle such that a relative displacement between the turbine blade tips and the stator housing will produce a change in the blade tip clearance, the process comprising the steps of:
-
biasing the rotor shaft in a direction to increase the turbine blade tip clearance; producing a pressure force on the rotor discs of the engine to bias the rotor shaft in a direction to decrease the turbine blade tip clearance; and
,biasing the rotor shaft in a direction to increase the turbine blade tip clearance includes applying a compression spring to the rotor shaft. - View Dependent Claims (7, 8)
-
-
9. A process for controlling a blade tip clearance in a turbine of a gas turbine engine, the blade tips and a stator housing formed at an angle such that a relative displacement between the turbine blade tips and the stator housing will produce a change in the blade tip clearance, the process comprising the steps of:
-
biasing the rotor shaft in a direction to increase the turbine blade tip clearance; producing a pressure force on the rotor discs of the engine to bias the rotor shaft in a direction to decrease the turbine blade tip clearance; applying a counter weight bias to the rotor shaft to oppose the weight of the rotor shaft such that a lower differential pressure is required to displace the rotor shaft.
-
Specification