Temperature estimation apparatus for aeroplane gas turbine engine
First Claim
1. An apparatus for estimating temperature for an aeroplane gas turbine engine mounted on an aircraft and having a combustion chamber, a high-pressure turbine rotated by high-pressure gas exhausted from the combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas which has passed through the high-pressure turbine, comprising:
- a low-pressure turbine rotational speed sensor adapted to detect a rotational speed of the low-pressure turbine (N1);
an ambient temperature sensor adapted to detect an ambient temperature of the engine (T1);
an outlet temperature sensor adapted to detect an outlet temperature of the low-pressure turbine (EGT);
a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2);
an atmospheric pressure sensor adapted to detect an atmospheric pressure (P0);
an outlet temperature change calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on at least the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1);
a model outlet temperature difference calculator that calculates a model outlet temperature (MODEL-EGTC) based on at least a corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculates a model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature (T1);
a model outlet temperature difference correction amount calculator that calculates a correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) based on the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1); and
an inlet temperature estimation value calculator that calculates an estimation value of the low-pressure turbine inlet temperature (ITT) based on at least the detected low-pressure turbine outlet temperature (EGT), the calculated outlet temperature change (dEGT) and the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC),wherein the model outlet temperature difference calculator calculates the model outlet temperature (MODEL-EGTC) by retrieving second characteristics preset beforehand by the corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculates the model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from the corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature T1.
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Accused Products
Abstract
In a temperature estimation apparatus for an aeroplane gas turbine engine, there are provided with a calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on low-pressure turbine rotational speed (N1) and ambient temperature (T1), a calculator that calculates a model outlet temperature (MODEL-EGTC) based on corrected high-pressure turbine rotational speed (N2C) and atmospheric pressure (P0) to calculate a model outlet temperature difference (dEGTC) by subtracting the calculated temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC), a calculator that calculates a correction amount (dEGTad) relative to the model outlet temperature difference (dEGTC) based on the model outlet temperature difference (dEGTC) and low-pressure turbine rotational speed (N1), and a calculator that calculates an estimation value of the low-pressure turbine inlet temperature (ITT) based on the low-pressure turbine outlet temperature (EGT), etc., thereby enabling to estimate the inlet temperature of the low-pressure turbine.
18 Citations
21 Claims
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1. An apparatus for estimating temperature for an aeroplane gas turbine engine mounted on an aircraft and having a combustion chamber, a high-pressure turbine rotated by high-pressure gas exhausted from the combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas which has passed through the high-pressure turbine, comprising:
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a low-pressure turbine rotational speed sensor adapted to detect a rotational speed of the low-pressure turbine (N1); an ambient temperature sensor adapted to detect an ambient temperature of the engine (T1); an outlet temperature sensor adapted to detect an outlet temperature of the low-pressure turbine (EGT); a high-pressure turbine rotational speed sensor adapted to detect a rotational speed of the high-pressure turbine (N2); an atmospheric pressure sensor adapted to detect an atmospheric pressure (P0); an outlet temperature change calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on at least the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1); a model outlet temperature difference calculator that calculates a model outlet temperature (MODEL-EGTC) based on at least a corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculates a model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature (T1); a model outlet temperature difference correction amount calculator that calculates a correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) based on the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1); and an inlet temperature estimation value calculator that calculates an estimation value of the low-pressure turbine inlet temperature (ITT) based on at least the detected low-pressure turbine outlet temperature (EGT), the calculated outlet temperature change (dEGT) and the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC), wherein the model outlet temperature difference calculator calculates the model outlet temperature (MODEL-EGTC) by retrieving second characteristics preset beforehand by the corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculates the model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from the corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature T1. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. An apparatus for estimating temperature for an aeroplane gas turbine engine mounted on an aircraft and having a combustion chamber, a high-pressure turbine rotated by high-pressure gas exhausted from the combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas which has passed through the high-pressure turbine, comprising:
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means for detecting a rotational speed of the low-pressure turbine (N1); means for detecting an ambient temperature of the engine (T1); means for detecting an outlet temperature of the low-pressure turbine (EGT); means for detecting a rotational speed of the high-pressure turbine (N2); means for detecting an atmospheric pressure (P0); means for calculating a low-pressure turbine outlet temperature change (dEGT) based on at least the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1); means for calculating a model outlet temperature (MODEL-EGTC) based on at least a corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and for calculating a model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature (T1); means for calculating a correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) based on the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1); and means for calculating an estimation value of the low-pressure turbine inlet temperature (ITT) based on at least the detected low-pressure turbine outlet temperature (EGT), the calculated outlet temperature change (dEGT) and the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC), wherein the inlet temperature estimation value calculating means has an adder and calculates the estimation value of the low-pressure turbine inlet temperature (ITT) by adding the detected low-pressure turbine outlet temperature (EGT), the calculated outlet temperature change (dEGT) and the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) at the adder. - View Dependent Claims (9, 10, 11, 12, 13, 14)
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15. A method for estimating temperature for an aeroplane gas turbine engine mounted on an aircraft and having a combustion chamber, a high-pressure turbine rotated by high-pressure gas exhausted from the combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas which has passed through the high-pressure turbine, comprising the steps of:
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detecting a rotational speed of the low-pressure turbine (N1) using a low-pressure turbine rotational speed sensor; detecting an ambient temperature of the engine (T1) using an ambient temperature sensor; detecting an outlet temperature of the low-pressure turbine (EGT) using an outlet temperature sensor; detecting a rotational speed of the high-pressure turbine (N2) using a high-pressure turbine rotational speed sensor; detecting an atmospheric pressure (P0) using an atmospheric pressure sensor; calculating, using an outlet temperature change calculator, a low-pressure turbine outlet temperature change (dEGT) based on at least the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1); calculating, using a model outlet temperature difference calculator, a model outlet temperature (MODEL-EGTC) based on at least a corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculating a model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature (T1); calculating, using a model outlet temperature difference correction amount calculator, a correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) based on the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1); and calculating, using an inlet temperature estimation value calculator, an estimation value of the low-pressure turbine inlet temperature (ITT) based on at least the detected low-pressure turbine outlet temperature (EGT), the calculated outlet temperature change (dEGT) and the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC), wherein the step of model outlet temperature difference calculating calculates the model outlet temperature (MODEL-EGTC) by retrieving second characteristics preset beforehand by the corrected high-pressure turbine rotational speed (N2C) obtained by correcting the detected high-pressure turbine rotational speed (N2) by the detected ambient temperature (T1) and the detected atmospheric pressure (P0), and calculates the model outlet temperature difference (dEGTC) by subtracting the calculated model outlet temperature (MODEL-EGTC) from the corrected low-pressure turbine outlet temperature (EGTC) obtained by correcting the detected low-pressure turbine outlet temperature (EGT) by the detected ambient temperature T1. - View Dependent Claims (16, 17, 18, 19, 20, 21)
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Specification