# US 11,898,503 B2 · Method and system for determining an engine temperature > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,898,503 B2 - Document ID: US11898503B2 - Status: Granted - Kind: B2 - Application number: 18/070,728 - Filed: 2022-11-29 - Published: 2023-03-30 - Granted: 2024-02-13 - Earliest claimed: 2020-03-16 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Yves Cloutier - Web page: https://patentgrep.com/patent/US11898503B2 ## CPC - F02C 9/28: Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) - F02C 9/00: Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02C 9/20: by throttling; by adjusting vanes - F05D 2240/35: Combustors or associated equipment - F05D 2260/821: Parameter estimation or prediction - F05D 2270/301: Pressure - F05D 2270/3013: Outlet pressure - F05D 2270/303: Temperature - F05D 2270/3061: of the working fluid - F05D 2270/44: active, predictive, or anticipative - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract Methods and systems for determining an engine temperature for a gas turbine engine are provided. An estimated combustor temperature is determined based on at least one operating condition of the gas turbine engine and an estimated vane mass flow. A corrected vane mass flow is determined based on the estimated combustor temperature, the estimated vane mass flow, and a combustor pressure. The corrected vane mass flow is compared to a reference vane mass flow to obtain the mass flow correction factor. When a condition associated with the mass flow correction factor is not satisfied, the estimated combustor temperature is adjusted based on the mass flow correction factor to produce an adjusted combustor temperature; and the mass flow correction factor is updated based on the adjusted combustor temperature. When the condition associated with the mass flow correction factor is satisfied, the estimated combustor temperature is assigned as the engine temperature. ## Claims ### Claim 1 A method for determining an engine temperature for a gas turbine engine, comprising: determining an inner-turbine temperature based on a low-pressure spool output power, an engine output power, an inlet mass flow and an exhaust temperature; determining a vane mass flow and a compressor mass flow based on the inlet mass flow; determining a high-pressure compressor load based on the compressor mass flow, a high-pressure compressor temperature and a high-pressure compressor delivery temperature; determining an estimated combustor temperature based on the high-pressure compressor load, the inner-turbine temperature and the vane mass flow; determining a corrected vane mass flow based on the estimated combustor temperature; comparing the corrected vane mass flow to a reference vane mass flow to obtain a mass flow correction factor; iteratively correcting the mass flow correction factor using an adjusted inlet mass flow until a mass flow correction condition is satisfied; and when the mass flow correction factor satisfies the mass flow correction condition, outputting, via a controller associated with the gas turbine engine, a signal to assign the estimated combustor temperature as the engine temperature for assisting at least one of the controller and an operator of the gas turbine engine in modulating at least one of a fuel flow provided to the gas turbine engine, modulating a position and orientation of variable geometry mechanisms within the gas turbine engine, and modulating a bleed level of the gas turbine engine. ### Claim 2 (depends on 1) The method of claim 1, wherein the determining of the estimated combustor temperature for a combustor of the gas turbine engine is further based on at least one of a flight mission stage and the engine output power. ### Claim 3 (depends on 1) The method of claim 1, further comprising adjusting the vane mass flow based on the adjusted inlet mass flow. ### Claim 4 (depends on 1) The method of claim 1, wherein the inlet mass flow is received from an input or is based on the adjusted inlet mass flow. ### Claim 5 (depends on 1) The method of claim 1, further comprising adjusting the corrected vane mass flow based on an altitude of operation of the gas turbine engine. ### Claim 6 (depends on 1) The method of claim 1, further comprising adjusting the corrected vane mass flow based on a compressor bleed associated with a compressor of the gas turbine engine. ### Claim 7 (depends on 1) The method of claim 1, wherein the estimated combustor temperature is a temperature at an inlet of a high-pressure turbine of the gas turbine engine, the high-pressure turbine upstream of a low-pressure turbine of the gas turbine engine. ### Claim 8 (depends on 7) The method of claim 7, wherein the estimated combustor temperature is a temperature at a vane throat for the high-pressure turbine of the gas turbine engine. ### Claim 9 (depends on 1) The method of claim 1, wherein the engine temperature is an inter-turbine temperature, and wherein outputting the signal comprises generating the inter-turbine temperature by applying a scaling factor to the estimated combustor temperature and outputting the signal to cause the inter-turbine temperature to be displayed to the operator of the gas turbine engine. ### Claim 10 (depends on 1) The method of claim 1, wherein the mass flow correction condition comprises an evaluation of whether the mass flow correction factor is less than a threshold. ### Claim 11 (depends on 1) The method of claim 1, wherein the low-pressure spool output power is determined based on a power turbine speed and an engine output torque. ### Claim 12 (depends on 1) The method of claim 1, wherein the engine temperature is used by the controller to monitor a maximum temperature in a thermodynamic cycle of the gas turbine engine during operation of the gas turbine engine. ### Claim 13 A system for determining an engine temperature of a gas turbine engine, comprising a combustor temperature estimator receiving at least one operating condition of the gas turbine engine and producing an estimated combustor temperature; a vane mass flow estimator producing a vane mass flow to the combustor temperature estimator; a combustor pressure determiner producing a combustor pressure; a vane mass flow corrector receiving the estimated combustor temperature from the combustor temperature estimator, the vane mass flow from the vane mass flow estimator and the combustor pressure from the combustor pressure determiner, the vane mass flow corrector determining a corrected vane mass flow; a vane mass flow comparator receiving the corrected vane mass flow from the vane mass flow corrector, the vane mass flow comparator comparing the corrected vane mass flow to a reference vane mass flow for obtaining a mass flow correction factor; and a controller associated with the gas turbine engine updating the mass flow correction factor using an adjusted inlet mass flow until a mass flow correction condition is satisfied, and when the mass flow correction factor satisfies the mass flow correction condition, the controller outputting a signal to assign the estimated combustor temperature as the engine temperature for assisting at least one of the controller and an operator of the gas turbine engine in modulating at least one of a fuel flow provided to the gas turbine engine, modulating a position and orientation of variable geometry mechanisms within the gas turbine ermine, and modulating a bleed level of the gas turbine engine. ### Claim 14 (depends on 13) The system of claim 13, wherein the vane mass flow comparator further provides the mass flow correction factor to the combustor temperature estimator. ### Claim 15 (depends on 13) The system of claim 13, wherein the combustor temperature estimator adjusts the estimated combustor temperature based on the mass flow correction factor. ### Claim 16 (depends on 13) The system of claim 13, wherein the estimated combustor temperature is a temperature at an inlet of a high-pressure turbine of the gas turbine engine, the high-pressure turbine upstream of a low-pressure turbine of the gas turbine engine. ### Claim 17 (depends on 16) The system of claim 16, wherein the estimated combustor temperature is a temperature at a vane throat for the high-pressure turbine of the gas turbine engine. ### Claim 18 (depends on 17) The system of claim 17, wherein the mass flow correction condition comprises an evaluation of whether the mass flow correction factor is less than a threshold. ### Claim 19 (depends on 13) The system of claim 13, wherein the at least one operating condition of the gas turbine engine comprises at least one of a flight mission stage and an engine power level. ### Claim 20 (depends on 13) The system of claim 13, wherein the vane mass flow is based on an inlet mass flow for an inlet of the gas turbine engine.