Turbine arrangement

• US 10,641,126 B2
• Filed: 06/14/2017
• Issued: 05/05/2020
• Est. Priority Date: 07/05/2016
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Mason, John R, Brown, David E
• Primary Examiner(s): Lee, Jr., Woody A
• Assistant Examiner(s): Delrue, Brian Christopher
• Application Number:
  US15/622,659
• Publication Number:
  US 20180010479A1
• Time in Patent Office: 1,056 Days
• Field of Search: 416 61
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/02 Shutting-down responsive to overspeed
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/329 in helicopters
• CPC Class Codes: G01P 3/481 of pulse signals

Abstract

A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

Claims

1. A turbine arrangement for a gas turbine engine comprising:

a turbine shaft;

an axial array of turbine rotors, the axial array having first and second axial ends defined by first and second turbine rotors respectively of the axial array of turbine rotors, each of the first and second turbine rotors in the axial array of turbine rotors being adjacent to at least one other turbine rotor to form one or more pairs of adjacent turbine rotors, wherein the one or more pairs of adjacent turbine rotors is between the first and second turbine rotors, and any given pair of the adjacent turbine rotors are coupled together to transmit drive therebetween;

a drive arm directly coupled to the turbine shaft and the axial array of turbine rotors at the first turbine rotor only; and

a measurement system arranged to measure a parameter indicative of rotational speed of the second axial end of the axial array of turbine rotors.

2. The turbine arrangement as claimed in claim 1, wherein each turbine rotor of the axial array of turbine rotors is mounted to a respective disc, and the drive arm is coupled to the disc to which the first turbine rotor is mounted.

3. The turbine arrangement as claimed in claim 1, wherein the axial array of turbine rotors comprises at least two turbine rotors.

4. The turbine arrangement as claimed in claim 1, wherein the axial array of turbine rotors comprises at least three turbine rotors.

5. The turbine arrangement as claimed in claim 1, further comprising a respective interstage spacer between each adjacent pair of turbine rotors, each spacer arranged to transmit drive.

6. The turbine arrangement as claimed in claim 1, wherein the measurement system comprises a phonic wheel and a magnetic inductance speed sensor.

7. The turbine arrangement as claimed in claim 1, wherein there exists no turbine rotors of the axial array that are axially forward of a connection provided by the drive arm.

8. A gas turbine engine comprising the turbine arrangement as claimed in claim 1.

9. The gas turbine engine as claimed in claim 8, further comprising a controller configured to compare the measured parameter to a comparison parameter and to implement mitigation action if the measured parameter exceeds the comparison parameter.

10. The gas turbine engine as claimed in claim 9, wherein the mitigation action consists of any one or a combination of:

reduce fuel flow to the engine;

shut-off fuel flow to the engine;

shut down the engine;

reduce the rotational speed of the turbine shaft.

11. The gas turbine engine as claimed in claim 9, wherein the comparison parameter is a comparison speed.

12. The gas turbine engine as claimed in claim 11, wherein the comparison speed is an expected speed determined from a model or empirical data corresponding to normal operation of the engine.

13. The gas turbine engine as claimed in claim 11, wherein the comparison speed is a threshold speed, which is an absolute value or is dependent on engine thrust demand.