# US 10,371,000 B1 · Flush-mount combined static pressure and temperature probe > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,371,000 B1 - Document ID: US10371000B1 - Status: Granted - Kind: B1 - Application number: 15/934,615 - Filed: 2018-03-23 - Granted: 2019-08-06 - Earliest claimed: 2018-03-23 - Assignees: Rosemount Aerospace Inc. - Applicants: Rosemount Aerospace Inc. - Inventors: Lisa Graham - Web page: https://patentgrep.com/patent/US10371000B1 ## CPC - F01D 17/085: {to temperature} - F01D 17/08: responsive to condition of working-fluid, e.g. pressure - F23N 5/022: {using electronic means (F23N5/04 - F23N5/14 take precedence)} - F23N 5/24: Preventing development of abnormal or undesired conditions, i.e. safety arrangements (F23N5/02 - F23N5/18 take precedence) - F23R 3/46: Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings - G01K 13/028: {for use in total air temperature [TAT] probes} - G01L 19/0092: {Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature (G01L9/025, G01L9/045, G01L9/065, G01L9/085, G01L9/105, G01L9/125, G01L19/02, G01L19/04 take precedence; measuring two or more variable G01D21/02; temperature sensors with pressure compensation G01K1/26)} - G01P 5/14: by measuring differences of pressure in the fluid - G01P 13/025: {indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw} - F05D 2270/301: Pressure - F05D 2270/3011: Inlet pressure - F05D 2270/303: Temperature - F05D 2270/312: Air pressure - F05D 2270/313: Air temperature - F05D 2270/80: Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges - F23N 2225/04: pressure - F23N 2225/21: outlet temperature - F23N 2241/20: Gas turbines - G01L 19/0681: {Protection against excessive heat} - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F23N: REGULATING OR CONTROLLING COMBUSTION (control devices specially adapted for combustion apparatus in which combustion takes place in a fluidised bed of fuel or other particles F23C10/28; condition responsive controls for regulating combustion in domestic stoves with open fires for solid fuel F24B1/187) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - G01K: MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR (radiation pyrometry G01J5/00) - G01L: MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE (weighing G01G) - G01P: MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT (measuring or recording blood flow A61B5/02, A61B8/06; monitoring speed or deceleration of electrically-propelled vehicles B60L3/00; vehicle lighting systems adapted to indicate speed B60Q1/54; determining position or course in navigation, measuring ground distance in geodesy or surveying G01C; combined measuring devices for measuring two or more variables of movement G01C23/00; measuring velocity of sound G01H; measuring velocity of light G01J7/00; measuring direction or velocity of solid objects by reception or emission of radiowaves or other waves and based on propagation effects, e.g. Doppler effect, propagation time, direction of propagation, G01S; measuring speed of nuclear radiation G01T; measuring acceleration of gravity G01V; {measuring or recording the speed of trains B61L23/00; speed indicators incorporated in motor vehicles B60K35/00; measuring frequency or phase G01R; traffic control G08G}) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A pressure and temperature probe includes a probe head, a probe tip extending from the probe head and ending with a sensor face, a pressure channel extending into the probe tip through the sensor face, and a temperature channel extending into the probe tip through the sensor face. A pressure sensor is in fluid communication with a pressure channel and a temperature sensor in fluid communication with the temperature channel. The temperature channel extends parallel to the pressure channel, and the temperature channel is fluidly separate from the pressure channel. The sensor face can be configured to minimally intrude the flowpath of a working fluid, thereby minimizing disruption of the flowpath. The probe can be configured on a gas turbine engine. ## Claims ### Claim 1 A gas turbine engine extending along an axis comprising: a fan section comprising a plurality of rotor cascades and a plurality of stator cascades; a splitter downstream of the fan section, the splitter including an inner side, an outer side, and an inside surface; a compressor section downstream of the splitter; a combustor section downstream of the compressor section; a first turbine section downstream of the combustor section, the first turbine section being connected to the compressor section; a second turbine section downstream of the first turbine section, the second turbine section being connected to the fan section; and a probe assembly comprising: a probe tip including a sensor face; a pressure channel extending into the probe tip through the sensor face; and a temperature channel extending into the probe tip through the sensor face; a pressure sensor in fluid communication with a pressure channel; and a temperature sensor in fluid communication with the temperature channel; wherein: the temperature channel is substantially parallel to the pressure channel; and the sensor face is substantially flush with the inner side of the splitter. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the sensor face is offset no more than 0.76 mm from the inside surface of the splitter. ### Claim 3 (depends on 1) The gas turbine engine of claim 1, wherein the pressure sensor is a static pressure sensor. ### Claim 4 (depends on 1) The gas turbine engine of claim 1, wherein the temperature sensor is a total temperature sensor. ### Claim 5 (depends on 1) The gas turbine engine of claim 1, wherein the temperature channel includes an exit port positioned inside of the splitter. ### Claim 6 (depends on 1) The gas turbine engine of claim 1, wherein the temperature channel includes an exit port positioned outside of the splitter. ### Claim 7 (depends on 1) The gas turbine engine of claim 1, wherein a center of the temperature channel at the sensor face is in substantially the same axial position as a center of the pressure channel at the sensor face. ### Claim 8 A probe comprising: a probe head; a probe tip extending from the probe head and ending with a sensor face; a pressure channel extending into the probe tip through the sensor face; a pressure sensor in fluid communication with a pressure channel; a temperature channel extending into the probe tip through the sensor face; and a temperature sensor in fluid communication with the temperature channel; wherein: the temperature channel extends parallel to the pressure channel; and the temperature channel is fluidly separate from the pressure channel. ### Claim 9 (depends on 8) The probe of claim 8, wherein a center of the temperature channel at the sensor face is in substantially the same axial position as a center of the pressure channel at the sensor face. ### Claim 10 (depends on 8) The probe of claim 8, wherein the pressure sensor is a static pressure sensor. ### Claim 11 (depends on 8) The probe of claim 8, wherein the temperature sensor is a total temperature sensor. ### Claim 12 (depends on 8) The probe of claim 8, further comprising: an exit port in fluid communication with the temperature channel, the exit port extending through the probe tip distal from the sensor face. ### Claim 13 (depends on 8) The probe of claim 8, further comprising: a duct extending between the temperature sensor and the probe head that is fluidly separate from the pressure channel. ### Claim 14 (depends on 8) A gas turbine engine extending along an axis comprising: a fan section comprising a plurality of rotor cascades and a plurality of stator cascades; a compressor section downstream of the fan section; a combustor section downstream of the compressor section; a first turbine section downstream of the combustor section, the first turbine section being connected to the compressor section; a second turbine section downstream of the first turbine section, the second turbine section being connected to the fan section; and the probe of claim 8. ### Claim 15 A gas turbine engine extending along an axis comprising: a fan section comprising a plurality of rotor cascades and a plurality of stator cascades; a splitter downstream of the fan section, the splitter including inner side, an outer side, and an inside surface; a compressor section downstream of the fan section; a combustor section downstream of the compressor section; a first turbine section downstream of the combustor section, the first turbine section being connected to the compressor section; a second turbine section downstream of the first turbine section, the second turbine section being connected to the fan section; and a probe assembly comprising: a probe tip including a sensor face; a pressure channel extending into the probe tip through the sensor face; a pressure sensor in fluid communication with a pressure channel; a temperature channel extending into the probe tip through the sensor face; and a temperature sensor in fluid communication with the temperature channel; wherein the temperature channel extends substantially parallel to the pressure channel. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the pressure sensor is a static pressure sensor. ### Claim 17 (depends on 15) The gas turbine engine of claim 15, wherein the sensor face offset no more than 0.76 mm from the inside surface of the splitter. ### Claim 18 (depends on 15) The gas turbine engine of claim 15, wherein the temperature channel includes an outlet positioned inside of the splitter. ### Claim 19 (depends on 15) The gas turbine engine of claim 15, wherein the temperature channel includes an outlet positioned outside of the splitter. ### Claim 20 (depends on 15) The gas turbine engine of claim 15, wherein a center of the temperature channel at the sensor face is in substantially the same axial position as a center of the pressure channel at the sensor face.