TEMPERATURE ESTIMATION APPARATUS FOR AEROPLANE GAS TURBINE ENGINE

• US 20120072091A1
• Filed: 09/15/2011
• Published: 03/22/2012
• Est. Priority Date: 09/16/2010
• Status: Active Grant

• Current Assignee: Honda Motor Co., Ltd. (Honda Motor Company)
• Original Assignee: Honda Motor Co., Ltd. (Honda Motor Company)
• Inventors: Muramatsu, Hironori, Saita, Tomohisa
• Granted Patent: US 8,731,798 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: G01K 13/02 for measuring temperature of moving fluids or granular materials capable of flow
• CPC Class Codes: G01K 13/024 of moving gases
• CPC Class Codes: G01K 7/42 Circuits effecting compensation of thermal inertia; Circuits for predicting the stationary value of a temperature

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.

Claims

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).

2. The apparatus according to claim 1, wherein the outlet temperature change calculator calculates the low-pressure turbine outlet temperature change (dEGT) by retrieving first characteristics preset beforehand by the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1).

3. The apparatus according to claim 2, wherein the first characteristics are preset such that the low-pressure turbine outlet temperature change (dEGT) increases with increasing low-pressure turbine rotational speed (N1) and decreases with increasing ambient temperature (T1).

4. The apparatus according to claim 1, 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.

5. The apparatus according to claim 4, wherein the second characteristics are preset such that the model outlet temperature (MODEL-EGTC) increases with increasing 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 decreases with increasing atmospheric pressure (P0).

6. The apparatus according to claim 1, wherein the model outlet temperature difference correction amount calculator calculates the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) by retrieving third characteristics preset beforehand by the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1).

7. The apparatus according to claim 6, wherein the third characteristics are preset such that the correction amount (dEGTad) increases with increasing model outlet temperature difference (dEGTC) and increasing low-pressure turbine rotational speed (N1).

8. The apparatus according to claim 1, wherein the inlet temperature estimation value calculator 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.

9. 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:

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).

10. The apparatus according to claim 9, wherein the outlet temperature change calculating means calculates the low-pressure turbine outlet temperature change (dEGT) by retrieving first characteristics preset beforehand by the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1).

11. The apparatus according to claim 10, wherein the first characteristics are preset such that the low-pressure turbine outlet temperature change (dEGT) increases with increasing low-pressure turbine rotational speed (N1) and decreases with increasing ambient temperature (T1).

12. The apparatus according to claim 9, wherein the model outlet temperature difference calculating means 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.

13. The apparatus according to claim 12, wherein the second characteristics are preset such that the model outlet temperature (MODEL-EGTC) increases with increasing 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 decreases with increasing atmospheric pressure (P0).

14. The apparatus according to claim 9, wherein the model outlet temperature difference correction amount calculating means calculates the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) by retrieving third characteristics preset beforehand by the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1).

15. The apparatus according to claim 14, wherein the third characteristics are preset such that the correction amount (dEGTad) increases with increasing model outlet temperature difference (dEGTC) and increasing low-pressure turbine rotational speed (N1).

16. The apparatus according to claim 9, 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.

17. 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:

detecting a rotational speed of the low-pressure turbine (N1);

detecting an ambient temperature of the engine (T1);

detecting an outlet temperature of the low-pressure turbine (EGT);

detecting a rotational speed of the high-pressure turbine (N2);

detecting an atmospheric pressure (P0);

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);

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 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 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 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).

18. The method according to claim 17, wherein the step of outlet temperature change calculating calculates the low-pressure turbine outlet temperature change (dEGT) by retrieving first characteristics preset beforehand by the detected low-pressure turbine rotational speed (N1) and the ambient temperature (T1).

19. The method according to claim 18, wherein the first characteristics are preset such that the low-pressure turbine outlet temperature change (dEGT) increases with increasing low-pressure turbine rotational speed (N1) and decreases with increasing ambient temperature (T1).

20. The method according to claim 17, 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.

21. The method according to claim 20, wherein the second characteristics are preset such that the model outlet temperature (MODEL-EGTC) increases with increasing 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 decreases with increasing atmospheric pressure (P0).

22. The method according to claim 17, wherein the step of model outlet temperature difference correction amount calculating calculates the correction amount (dEGTad) relative to the calculated model outlet temperature difference (dEGTC) by retrieving third characteristics preset beforehand by the calculated model outlet temperature difference (dEGTC) and the detected low-pressure turbine rotational speed (N1).

23. The method according to claim 22, wherein the third characteristics are preset such that the correction amount (dEGTad) increases with increasing model outlet temperature difference (dEGTC) and increasing low-pressure turbine rotational speed (N1).

24. The method according to claim 17, wherein the step of inlet temperature estimation value calculating 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 an adder.