# US 10,480,342 B2 · Gas turbine engine with health monitoring system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,342 B2 - Document ID: US10480342B2 - Status: Granted - Kind: B2 - Application number: 15/000,636 - Filed: 2016-01-19 - Published: 2017-07-20 - Granted: 2019-11-19 - Earliest claimed: 2016-01-19 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce Corporation; Rolls-Royce North American Technologies, Inc. - Inventors: Bruce E. Varney; Jack D. Petty; Daniel K. Vetters; Eugene Clemens - Web page: https://patentgrep.com/patent/US10480342B2 ## CPC - F01D 11/24: by selectively cooling-heating stator or rotor components - F01D 17/085: {to temperature} - F05D 2240/11: Shroud seal segments - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/201: by impingement of a fluid - F05D 2260/80: Diagnostics - F05D 2300/6033: Ceramic matrix composites [CMC] - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) 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. ### Claim 4 (depends on 1) The gas turbine engine of claim 1, wherein the second end of the pressure tube extends into the outer pin receiver. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 5) 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. ### Claim 7 (depends on 1) 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. ### Claim 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. ### Claim 9 (depends on 8) 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. ### Claim 10 (depends on 9) 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. ### Claim 11 (depends on 9) 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. ### Claim 12 (depends on 8) 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. ### Claim 13 (depends on 12) 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. ### Claim 14 (depends on 8) 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. ### Claim 15 (depends on 14) The turbine shroud of claim 14, wherein the second end of the pressure tube extends into the outer pin receiver. ### Claim 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. ### Claim 17 (depends on 16) The method of claim 16, wherein the health monitoring system further includes a conduit arranged to direct the pressurized cooling air into the buffer chamber and the valve is connected to the conduit. ### Claim 18 (depends on 17) The method of claim 17, 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 a predetermined threshold pressure. ### Claim 19 (depends on 16) The method of claim 16, wherein the carrier is formed to include a high-pressure cooling air passageway that extends through the carrier and the method further includes directing high-pressure air through the high-pressure cooling air passageway toward the annular runner, the high-pressure air having a greater pressure than the pressurized cooling air.