Method and apparatus for sealing components of a gas turbine engine with a dielectric barrier discharge plasma actuator

Patent metadata

Field	Value
Publication number	US-10487679-B2
Application number	US-201715651745-A
Country	US
Kind code	B2
Filing date	Jul 17, 2017
Priority date	Jul 17, 2017
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A system and method for aerodynamically sealing rotating and fixed components of a gas turbine engine. The system includes a gas turbine engine having a casing and a rotating portion, a plasma actuator having a first and a second electrodes, the first electrode including at least one section of substantially flat conductive material encased in a dielectric material forming at least a portion of a cylinder disposed circumferentially on the casing. The system also includes the rotating portion operably configured as the second electrode, and an excitation source operably connected between the first electrode and the second electrode, the excitation source generating an excitation signal and applying it to the first and second electrodes to cause the actuator to form a plasma between the first and second electrodes, the plasma inducing an airflow between the casing and the rotating portion.

First claim

What is claimed is:

1. A non-contacting method for aerodynamically sealing rotating and fixed components of a gas turbine engine with a dielectric barrier discharge plasma actuator having a first electrode and a second electrode, the method comprising:
disposing the first electrode circumferentially on a casing of the gas turbine engine, the first electrode comprising at least one section of substantially flat conductive material encased in a dielectric material generally forming a cylinder;
configuring a rotating portion of the gas turbine engine as the second electrode;
operably connecting an excitation source between the first electrode and the second electrode; and
generating an excitation signal with the excitation source and applying it to the first and second electrode to cause the actuator to form plasma between the first and second electrode, the plasma inducing an airflow between the casing and the rotating portion,
wherein the disposing includes applying the first electrode to at least a portion of an inner circumference of the casing such that the first electrode extends continuously thereabout and forms a cylinder around a circumference of the casing.

2. The method of claim 1 , wherein the disposing includes placing the first electrode forward axially of the second electrode, and thereby the plasma generated is uniform along an entire circumference of the casing and induces an airflow forward axially.

3. The method of claim 1 , wherein the plasma is substantially uniform in at least one of an entire circumference of the casing and an axial direction.

4. The method of claim 1 , wherein the generating includes grounding a rotating blade included with the rotating portion to a ground potential such that the rotating blade itself is configured as the second electrode, and providing an alternating current (AC) signal to the actuator.

5. The method of claim 1 , wherein the rotating portion is at least on one of a fan blade, a compressor blade, a turbine blade, and a raised portion on a spool.

6. The method of claim 1 , further including executing a method to control excitation signal to the actuator to control and manipulate the plasma generated and thereby the airflow induced, wherein the control is based on an operating condition of the gas turbine engine.

7. The method of claim 1 , further including measuring an operating parameter of the gas turbine engine.

8. The method of claim 7 , further including diagnosing a condition of the gas turbine engine based on at least the measuring of the operating parameter of the gas turbine engine.

9. The method of claim 8 , wherein the diagnosing includes at least one of collecting data over time to facilitate making lifetime predictions of performance of the gas turbine engine.

10. The system of claim 1 , wherein, the plasma is substantially uniform in at least one of an entire circumference of the casing and an axial direction.

11. A system for aerodynamically sealing rotating and fixed components of a gas turbine engine comprising:
a gas turbine engine having a casing and a rotating portion;
a dielectric barrier discharge plasma actuator having a first electrode and a second electrode, the first electrode disposed circumferentially on the casing of the gas turbine engine, the first electrode comprising at least one section of substantially flat conductive material encased in a dielectric material generally forming at least a portion of a cylinder;
a rotating portion configured as the second electrode; and
an excitation source operably connected between the first electrode and the second electrode, the excitation source generating an excitation signal and applying it to the first and second electrode to cause the actuator to form plasma between the first and second electrode, the plasma inducing an airflow between the casing and the rotating portion,
wherein the first electrode is disposed on at least a portion of an inner circumference of the casing and extends continuously thereabout so as to form a cylinder around a circumference of the casing.

12. The system of claim 11 , wherein the first electrode is placed forward axially of the second electrode.

13. The system of claim 11 , wherein the rotating portion includes at least on one of a fan blade, a compressor blade, a turbine blade, and a raised portion on a spool.

14. The system of claim 11 , wherein the rotating portion is including a plurality of stages of a plurality of rotating blades.

15. The system of claim 11 , wherein a rotating blade included with the rotating portion is coupled to a ground potential such that the rotating blade itself is the second electrode, and wherein the excitation signal is an alternating current (AC) signal with its common or ground connected to the second electrode.

16. The system of claim 15 , wherein the alternating current (AC) signal is at least one of a sinusoid and exhibits a frequency sufficiently high in relation to any relevant dynamics for the flow, so that an associated aerodynamic force produced by plasma 30 is effectively steady state.

17. The system of claim 11 , further including a controller operably connected to at least one of the actuator, the excitation source, and a plurality of sensors configured to measure an operating parameter of the gas turbine engine.

18. The system of claim 17 , wherein the controller includes the excitation source.

19. The system of claim 17 , further including the controller executing a method to control excitation signal to the actuator to control and manipulate the plasma generated and thereby the airflow induced, wherein the control is based on an operating condition of the gas turbine engine.

20. The system of claim 19 , further including the controller executing a method to diagnose a condition of the gas turbine engine based on at least the measuring of an operating parameter of the gas turbine engine.

21. The system of claim 20 , wherein the diagnosing includes at least one of collecting data over time to facilitate making lifetime predictions of performance of the gas turbine engine.

Assignees

• United Technologies Corp

Inventors

• Bagdonis Guthrie

Classifications

• F01D11/10

  using sealing fluid, e.g. steam · CPC title

• F05D2270/172

  by a plasma generator, e.g. control of ignition · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F01D11/20 Primary

  Actively adjusting tip-clearance · CPC title

• F01D11/025

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title