# US 2018/0320700 A1 · Turbine Engine Compressor with a Turbulence Sensor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0320700 A1 - Document ID: US20180320700A1 - Status: Published application - Kind: A1 - Application number: 15/970,325 - Filed: 2018-05-03 - Published: 2018-11-08 - Earliest claimed: 2017-05-05 - Assignees: Safran Aero Boosters SA - Applicants: Safran Aero Boosters SA - Inventors: Stéphane Hiernaux - Web page: https://patentgrep.com/patent/US20180320700A1 ## CPC - F04D 27/001: {Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring} - F01D 17/02: Arrangement of sensing elements - F01D 17/085: {to temperature} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - F05D 2220/3217: for the first stage of a compressor or a low pressure compressor - F05D 2240/121: related to the leading edge of a stator vane - F05D 2270/10: to cope with, or avoid, compressor flow instabilities - F05D 2270/101: Compressor surge or stall - F05D 2270/301: Pressure - F05D 2270/3011: Inlet pressure - F05D 2270/303: Temperature - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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 system for measuring turbulence of a flow of a turbine engine, notably of a turbine engine compressor includes a first housing with a first pressure sensor and a first inlet, a second housing with a second pressure sensor and a second inlet inclined relative to the first inlet, and a temperature sensor. The system is configured to calculate at least two orientation components of the velocity of the flow on the basis of the pressure sensors and the temperature sensor. The inlets are disposed at the vane foot, on the leading edge at the level of an internal shell. ## Claims ### Claim 1 Compressor of a turbine engine, the compressor comprising: an upstream air intake for an air flow; an annular row of vanes; and a system for measuring turbulences in said air flow, the turbulence measuring system comprising: a first housing receiving a first pressure sensor and a first inlet, a second housing receiving a second pressure sensor and a second inlet inclined relative to the first inlet; and a temperature sensor, wherein the first and second inlet are received in the same vane of the annular row of vane, said vane having a radial height, and the first and second inlet being positioned within at most: 30%, or 10%, or 5% of the radial height of said vane; the system being configured to continuously calculate at least two orientation components of the velocity of the air flow on the basis of the pressure sensors and the temperature sensor. ### Claim 2 (depends on 1) Compressor according to claim 1, wherein the at least two orientation components of the velocity of the flow comprise: an axial component, and/or a radial component, and/or a circumferential component. ### Claim 3 (depends on 1) Compressor according to claim 1, wherein the first housing, the first sensor and the first inlet are configured to measure the total pressure of the flow. ### Claim 4 (depends on 1) Compressor according to claim 1, wherein the second housing, the second sensor and the second inlet are configured to measure the static pressure of the flow. ### Claim 5 (depends on 1) Compressor according to claim 1, further comprising: a third housing with a third pressure sensor and a third inlet, each of the first, second, and third inlets being inclined relative to each other. ### Claim 6 (depends on 1) Compressor according to claim 1, wherein the inlets comprise: tubes, said tubes being inclined relative to one another. ### Claim 7 (depends on 1) Compressor according to claim 1, further comprising: a plurality of second housings, each with a second pressure sensor and a second inlet, each inlet being inclined relative to the other inlets. ### Claim 8 (depends on 7) Compressor according to claim 7, wherein the second housings are arranged around the first housing. ### Claim 9 (depends on 1) Compressor according to claim 1, further comprising: a one-piece body in which the housings and the inlets are formed, and in which the sensors are received. ### Claim 10 (depends on 1) Compressor according to claim 1, wherein the housings are blind and/or separated from one another in a sealed manner by the body. ### Claim 11 (depends on 1) Compressor according to claim 1, wherein the system is configured to measure a level of disturbance as a function of the variations of the orientation components of the velocity of the flow. ### Claim 12 (depends on 1) Compressor according to claim 1, further comprising: a unit for calculating the orientation components with a calculation frequency greater than or equal to: 300 Hz, or 800 Hz, or 10 kHz for each orientation component. ### Claim 13 (depends on 1) Compressor according to claim 1, wherein the pressure sensors are electric sensors, and/or the temperature sensor is an electric sensor. ### Claim 14 (depends on 1) Compressor according to claim 1, wherein the vanes have leading edges, the inlets of the housings being disposed axially at the level of the leading edges. ### Claim 15 (depends on 14) Compressor according to claim 14, wherein the inlets of the housings are arranged radially along the same leading edge of a vane in order to measure there the at least two flow speed components. ### Claim 16 (depends on 1) Compressor according to claim 1, further comprising: an internal shell connected to the vane, the inlets of the housings being disposed radially at the height of the shell. ### Claim 17 Compressor of a turbine engine, the compressor comprising: an upstream air intake for an air flow; an annular row of vanes; and a system for measuring turbulences in said air flow, each vane of the annular row of vane having a leading edge, the turbulence measuring system comprising: a first housing receiving a first pressure sensor and a first inlet, a second housing receiving a second pressure sensor and a second inlet inclined relative to the first inlet, wherein the first inlet and the second inlet are arranged radially along the leading edge of the same a vane; and a temperature sensor; wherein the system is configured to calculate at least two orientation components of the velocity of the air flow on the basis of the pressure sensors and the temperature sensor. ### Claim 18 A turbine engine, comprising: an upstream air intake for an air flow; an annular row of vanes; and a system for measuring turbulences in said air flow, the turbulence measuring system comprising: a first housing receiving a first pressure sensor and a first inlet, a second housing receiving a second pressure sensor and a second inlet inclined relative to the first inlet; and a temperature sensor, wherein the first and second inlet are received in the same vane of the annular row of vane, said vane having a radial height, and the first and second inlet being positioned within at most: 30%, or 10%, or 5% of the radial height of said vane; the system being configured to continuously calculate at least two orientation components of the velocity of the air flow on the basis of the pressure sensors and the temperature sensor; and a fan axially facing at least one inlet of a housing of the turbulence measuring system.