Rotor thrust balance activated tip clearance control system

• US 7,909,566 B1
• Filed: 04/17/2007
• Issued: 03/22/2011
• Est. Priority Date: 04/20/2006
• Status: Expired due to Fees

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Brostmeyer, Joseph
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US11/787,560
• Time in Patent Office: 1,435 Days
• Field of Search: 415/131, 415/132, 415/34, 415/14, 415/107, 415/104, 415/106, 415/26, 415/96, 415/105, 415/129, 415/140, 415/219.1
• US Class Current: 415/34
• CPC Class Codes: F01D 11/22 by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• CPC Class Codes: F01D 25/168 for axial load mainly
• CPC Class Codes: F04D 29/052 Axially shiftable rotors F04D29/051 takes precedence ; control by creating a by-pass F04D27/0246
• CPC Class Codes: F05D 2260/52 involving springs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

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.

2. The gas turbine engine of claim 1, and further comprising:

the compressor comprises a centrifugal compressor with compressor blades that form a blade tip gap with a compressor blade tip shroud; and

,

the displacement of the rotor shaft to decrease the turbine blade tip gap also decreases the compressor blade tip gap.

3. The gas turbine engine of claim 2, and further comprising:

the centrifugal compressor rotor disc and the turbine blade rotor disc form pressure surfaces in which the pressure differential force is produced to displace the rotor shaft.

4. The gas turbine engine of claim 1, and further comprising:

a plurality of stages of turbine rotor discs with turbine blades extending from the rotor discs, each with a blade tip formed at an angle; and

,

a stator cone having substantially the same angle as the turbine blade tips such that relative displacement of the rotor shaft produces a change in the blade tip gap.

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.

7. The process for controlling a blade tip clearance in a turbine of a gas turbine engine of claim 6, and further comprising the step of:

biasing the rotor shaft in a direction to increase the turbine blade tip clearance includes orienting the rotor shaft in a vertical direction such that the weight of the rotor shaft produces the bias that increases the turbine blade tip clearance.

8. The process for controlling a blade tip clearance in a turbine of a gas turbine engine of claim 6, and further comprising the step of:

producing the pressure force on the rotor discs of the engine in which the pressure force is a function of an operating condition of the engine.

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.