Bowed rotor sensor system

• US 10,358,936 B2
• Filed: 07/05/2016
• Issued: 07/23/2019
• Est. Priority Date: 07/05/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Hockaday, Bruce, Haldeman, Charles W.
• Primary Examiner(s): Nguyen, Ninh H.
• Application Number:
  US15/201,716
• Publication Number:
  US 20180010480A1
• Time in Patent Office: 1,113 Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 19/02 dependent on temperature of component parts, e.g. of turbine-casing
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/06 Shutting-down
• CPC Class Codes: F01D 25/34 Turning or inching gear
• CPC Class Codes: F01D 5/12 Blades specially adapted for radial flow machines or engines F01D5/04; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F02C 7/262 Restarting after flame-out
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/804 Optical devices
• CPC Class Codes: G01B 21/16 for measuring distance of clearance between spaced objects

Abstract

According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

Claims

1. A bowed rotor sensor system for a gas turbine engine, the bowed rotor sensor system comprising:

a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine; and

a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data, and the controller is operable to control rotation of the gas turbine engine based on the bowed rotor status until the gap data received from the bowed rotor sensor meets a modulation amplitude threshold.

2. The bowed rotor sensor system as in claim 1, wherein the bowed rotor sensor is installed in a borescope port of the gas turbine engine.

3. The bowed rotor sensor system as in claim 2, wherein the observation region is aft of the borescope port.

4. The bowed rotor sensor system as in claim 1, wherein the bowed rotor sensor is an optical, acoustic, or microwave sensor.

5. The bowed rotor sensor system as in claim 1, wherein the controller is operable to compare the gap data to a baseline data set to determine the bowed rotor status and collect a time history of the gap data.

6. The bowed rotor sensor system as in claim 1, wherein the controller is operable to control a starter of the gas turbine engine based on the bowed rotor status.

7. The bowed rotor sensor system as in claim 1, wherein the controller is operable to control a core-turning motor of the gas turbine engine based on the bowed rotor status.

8. A bowed rotor sensor system for a gas turbine engine, the bowed rotor sensor system comprising:

a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine; and

a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data, wherein the gap data modulates as a rotor comprising the blades rotates within the gas turbine engine based on a changing gap between the air seal and the blade tip of the blades.

9. The bowed rotor sensor system as in claim 8, wherein the controller is operable to monitor an amplitude of modulation of the gap data to determine the bowed rotor status.

10. The bowed rotor sensor system as in claim 8, wherein collection of the gap data is synchronized with respect to a once-per-revolution indicator of the rotor.

11. A method of bowed rotor sensing for a gas turbine engine, the method comprising:

transmitting a sensing field from a bowed rotor sensor to an observation region within the gas turbine engine;

receiving a signal indicative of a gap between an air seal and a blade tip in the observation region;

monitoring, by a controller, a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region;

determining a bowed rotor status of the gas turbine engine based on the gap data; and

controlling rotation of the gas turbine engine based on the bowed rotor status until the gap data received from the bowed rotor sensor meets a modulation amplitude threshold.

12. The method as in claim 11, wherein the bowed rotor sensor is installed in a borescope port of the gas turbine engine.

13. The method as in claim 12, wherein the observation region is aft of the borescope port.

14. The method as in claim 11, wherein the bowed rotor sensor is an optical, acoustic, or microwave sensor.

15. The method as in claim 11, further comprising:

comparing the gap data to a baseline data set to determine the bowed rotor status; and

collecting a time history of the gap data.

16. The method as in claim 11, further comprising:

controlling a starter of the gas turbine engine based on the bowed rotor status.

17. The method as in claim 11, further comprising:

controlling a core-turning motor of the gas turbine engine based on the bowed rotor status.

18. A method of bowed rotor sensing for a gas turbine engine, the method comprising:

transmitting a sensing field from a bowed rotor sensor to an observation region within the gas turbine engine;

receiving a signal indicative of a gap between an air seal and a blade tip in the observation region;

monitoring, by a controller, a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region;

determining a bowed rotor status of the gas turbine engine based on the gap data; and

observing a modulation of the gap data as a rotor comprising the blades rotates within the gas turbine engine, the modulation indicative of a changing gap between the air seal and the blade tip of the blades.

19. The method as in claim 18, further comprising:

monitoring an amplitude of the modulation of the gap data to determine the bowed rotor status.

20. The method as in claim 18, wherein collection of the gap data is synchronized with respect to a once-per-revolution indicator of the rotor.