Gas turbine engine with health monitoring system

Patent metadata

Field	Value
Publication number	US-10480342-B2
Application number	US-201615000636-A
Country	US
Kind code	B2
Filing date	Jan 19, 2016
Priority date	Jan 19, 2016
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.

First claim

What is claimed is:

1. A gas turbine engine comprising
a turbine case arranged around a central axis of the gas turbine engine and formed to include an outer keyway extending in a radial direction through the turbine case,
an annular carrier formed to define a radially inwardly-opening carrier channel, the annular carrier including an outer pin receiver that extends through the annular carrier to allow pressurized cooling air to pass through the annular carrier into the radially inwardly-opening carrier channel,
a one-piece annular runner aligned axially with the annular carrier to block access into the radially inwardly-opening carrier channel and to cooperate with the radially inwardly-opening carrier channel to define a buffer chamber configured to receive the pressurized cooling air and to route the pressurized cooling air around the one-piece annular runner, and
a health monitoring system including a conduit configured to direct the pressurized cooling air through the turbine case and the annular carrier into the buffer chamber, a valve connected to the conduit, a pressure sensor configured to measure an air pressure in the buffer chamber, and a controller coupled to the valve to open and close the valve in response to signals received from the pressure sensor to modulate the pressurized cooling air directed into the buffer chamber,
wherein the pressure sensor includes a transducer located outside of the buffer chamber and a pressure tube having a first end coupled to the transducer and a second end in fluid communication with the buffer chamber and located in the buffer chamber such that the second end terminates in the buffer chamber.

2. The gas turbine engine of claim 1 , wherein the controller is configured to fully close the valve in response to the signals received from the pressure sensor being indicative of the air pressure in the buffer chamber being below a predetermined threshold pressure.

3. The gas turbine engine of claim 1 , wherein the controller is configured to fully open the valve in response to the signals received from the pressure sensor being indicative of the air pressure in the buffer chamber being below a predetermined threshold pressure.

4. The gas turbine engine of claim 1 , wherein the second end of the pressure tube extends into the outer pin receiver.

5. The gas turbine engine of claim 1 , wherein the annular carrier is formed to include a high-pressure cooling air passageway that extends through the annular carrier, the high-pressure cooling air passageway is configured to direct high-pressure air toward the one-piece annular runner, and the high-pressure air has a greater pressure than the pressurized cooling air.

6. The gas turbine engine of claim 5 , wherein the one-piece annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section and the high-pressure cooling air passageway is formed to direct the high-pressure air toward the forward section of the one-piece annular runner.

7. The gas turbine engine of claim 1 , wherein the controller and the valve are positioned radially outside the turbine case to locate the turbine case between the controller and the central axis.

8. A turbine shroud for use in a gas turbine engine having a central axis, the turbine shroud comprising
a carrier formed to define a radially inwardly-opening carrier channel, the carrier includes an outer pin receiver that extends through the carrier to allow pressurized cooling air to pass through the carrier into the carrier channel,
an annular runner aligned axially with the carrier to block access into the radially inwardly-opening carrier channel and to cooperate with the radially inwardly-opening carrier channel to define a buffer chamber configured to route the pressurized cooling air around the annular runner, and
a health monitoring system including a pressure sensor configured to measure an air pressure in the buffer chamber, a valve fluidly connected to the buffer chamber, and a controller coupled to the valve to open and close the valve to modulate the pressurized cooling air directed into the buffer chamber,
wherein the controller is configured to receive signals from the pressure sensor and to actuate the valve to increase the air pressure in the buffer chamber in response to the signals being indicative of the air pressure in the buffer chamber being below a predetermined threshold pressure.

9. The turbine shroud of claim 8 , wherein the turbine shroud further includes conduit in fluid communication with the outer pin receiver, the conduit arranged to direct the pressurized cooling air into the buffer chamber, and the conduit is connected to the valve.

10. The turbine shroud of claim 9 , wherein the controller is configured to receive signals from the pressure sensor and to fully close the valve in response to the signals being indicative of the air pressure in the buffer chamber being above the predetermined threshold pressure.

11. The turbine shroud of claim 9 , wherein the controller is configured to receive signals from the pressure sensor and to fully open the valve in response to the signals being indicative of the air pressure in the buffer chamber being below the predetermined threshold pressure.

12. The turbine shroud of claim 8 , wherein the carrier is formed to include a high-pressure cooling air passageway that extends through the carrier, the high-pressure cooling air passageway is configured to direct high-pressure air toward the annular runner, and the high-pressure air has a greater pressure than the pressurized cooling air.

13. The turbine shroud of claim 12 , wherein the annular runner includes a forward section, an aft section spaced apart axially from the forward section, and a midsection extending between the forward section and the aft section and the high-pressure cooling air passageway is formed to direct the high-pressure air toward the forward section of the annular runner.

14. The turbine shroud of claim 8 , wherein the pressure sensor includes a transducer located outside of the buffer chamber and a pressure tube having a first end coupled to the transducer and a second end that opens into the buffer chamber.

15. The turbine shroud of claim 14 , wherein the second end of the pressure tube extends into the outer pin receiver.

16. A method of controlling a health monitoring system included in a gas turbine engine, the method comprising
directing pressurized cooling air into a buffer chamber formed between a carrier and a one-piece annular runner included in a turbine shroud of the gas turbine engine, the buffer chamber configured to route the pressurized cooling air around the one-piece annular runner,
measuring an air pressure in the buffer chamber, and
controlling the pressurized cooling air directed into the buffer chamber in response to air pressure measurements,
wherein the health monitoring system includes a valve in fluid communication with the buffer chamber, a pressure sensor configured to measure an air pressure in the buffer chamber, and a controller coupled to the valve to open and close the valve to modulate the pressurize cooling air directed in to the buffer chamber and configured to receive signals from the pressure sensor and actuate the valve to increase the air pressure in the buffer chamber in response to the signals being indicative of the air pressure in the buffer chamber being below a predetermined threshold pressure.

17. The method of claim 16 , wherein the health monitoring system further in

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Varney Bruce E
• Petty Jack D
• Vetters Daniel K
• Clemens Eugene

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D17/085

  to temperature · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title