List of gas path measured parameters of the engine selected as test case.
Monitoring systems to predict the remaining lifetime of gas turbine engines are a major field of investigation, in particular, the monitoring systems that allow an on-line prediction. This chapter introduces and analyzes a new approach to develop mathematical models to estimate unmeasured parameters in an engine lifetime monitoring system; these models in contrast to previously developed models allow an on-line monitoring of unmeasured parameters, which are necessary to perform an on-line lifetime prediction. The blade of a high-pressure turbine (HPT) of a two-spool free turbine power plant is the test case. Several candidate models are developed for each unmeasured parameter; the best models are selected by their accuracy and robustness using the instrumental and truncation error as criteria. Ten faulty engine conditions are considered to analyze the model robustness. Two methods for model developing are compared; the first method uses physics-based models (proposed in this chapter), and the second method develops the models using the similarity concept (reference methodology). The results of the comparison show that the physics-based models are more robust to engine faults and overall they deliver a significantly more accurate prediction of the engine lifetime.
- gas turbine
- lifetime prediction
- model developing
- thermodynamic relations
- unmeasured parameters
Lifetime monitoring systems are an effective way to perform condition base maintenance of gas turbine engines [1, 2, 3]; this allows a better use of the available lifetime and improvement of the engine’s reliability.
Several approaches exist to predict the remaining lifetime, such as neural networks [4, 5, 6, 7], finite element analysis (FEA) [8, 9, 10], and statistical methods ; however, in order to significantly enhance the accuracy of the lifetime prediction, it is necessary to estimate the lifetime in real time (on-line prediction) using actual conditions [12, 13]. All of the previously cited approaches require a large amount of computing resources, making them not suitable for an on-line application; another limitation is that none of the cited approaches take into consideration the existing engine-to-engine differences and the performance deterioration.
Oleynik proposes in a study  an approach to perform on-line lifetime prediction of engine component condition (Figure 1); he proposes to use simple models to estimate the temperature and stresses at critical points. A major advantage of this approach is the use of actual engine operating and atmospheric conditions as input data. The methodology has been proven by practical application in monitoring of some Ukrainian engines.
As shown in Figure 1, one of the blocks performs the thermal condition (TC) monitoring, while the second block, the stress condition (SC) monitoring.
Inside the block of TC, it is necessary to set the thermal boundary conditions (gas temperature around the critical element and the heat transfer coefficient between the gas and metal), which are not measured parameters; the author  proposed a methodology to develop mathematical models based on the theory of similarity to estimate these boundary conditions.
In this chapter a new approach to develop physics-based models to estimate the unmeasured parameters is proposed and analyzed. This new approach emphasizes the accuracy of the models regardless of the engine-to-engine differences, taking into consideration a healthy and faulty engine condition.
With the help of the thermodynamic model of the engine chosen as test case, all the necessary data for model developing and validation is simulated; the simulation of the engine’s component degradation is widely used in gas turbine monitoring and diagnostics [15, 16].
A comparison between the physics-based models and the reference method based on the theory of similarity proposed by  is conducted to validate the accuracy of the methods.
Finally, the influence of the accuracy in the prediction of the thermal boundary conditions on the errors of the engine lifetime prediction is evaluated.
2. Test case
It is well-known that the thermomechanical stresses in gas turbine hot elements are very high, particularly in the turbine blade having a significant effect on the safety and economics of the fleet operation . For this reason, a turbine blade with three cooling channels has been chosen as the test case; the blade is mounted in the first stage of the high-pressure turbine (HPT) of a two-spool free turbine engine.
In Table 1 the seven measured gas path parameters of the engine chosen as test case are listed.
|Designation||Gas path parameter|
|Compressor discharge temperature|
|Compressor discharge pressure|
|HPT discharge temperature|
|HPT discharge pressure|
|Low-pressure turbine (LPT) discharge temperature|
|Rotational speed of the high-pressure (HP) rotor|
Experience has shown that it is sufficient to consider a two-dimensional analysis of the mid-span section of the blade in order to save computing time; however, the same methodological approach can be applied for a three-dimensional geometry.
The finite element model of the mid-span turbine blade section was built with the help of FEA software. After setting all the necessary boundary conditions, the distribution of the temperature and stresses was obtained. The critical points with the smallest safety factor were found as well; as shown in Figure 2, the critical points correspond to the numbers 101, 102, 103, and 69.
Three critical points are located at the leading edge of the blade and one critical point at the trailing edge. For an easier analysis, the four critical points are organized into two groups: group a (GA) contains the critical points 101, 102, and 103, and group b (GB) contains the critical point number 69.
The thermodynamic model of the engine chosen as test case  is used to generate all the data for model developing and validation.
3. Engine lifetime monitoring system
A brief description of the lifetime monitoring system proposed by the author  is presented to have a better understanding. As shown in Figure 1, the block to perform the TC contains the sub-block named “thermal boundary conditions” (unmeasured parameters). The new approach for model developing proposed in this chapter focuses all the efforts in improving the accuracy in this sub-block, as improving the efficiency in the prediction of the thermal boundary conditions directly affects the accuracy of the whole monitoring system.
In the following subsection, the simple mathematical models used to estimate the blade temperature and the thermal stress at the critical points are explained.
3.1 Turbine blade thermal and stress monitoring models
In  an analysis of the models proposed by  to estimate the blade temperature and stress applied to the same turbine blade and critical points was conducted. As a result, it was concluded that the best model to calculate the blade temperature at the critical points is:
Here is the blade temperature at the critical point, is the cooling temperature, is the heating temperature, is a dimensionless parameter, and is the relation of the heat transfer coefficients at current and reference engine operating modes:
Here and are the heat transfer coefficients at actual and reference engine working operating modes, respectively.
The model to estimate the thermal stress at critical points is:
Here is the thermal stress at the critical point, is a dimensionless parameter, and is the rotational speed.
The parameters , , and are unmeasured parameters, which further will be referred as thermal boundary conditions; since this unmeasured parameters are the input data in Eqs. (1) and (3), it is necessary to develop mathematical models for their prediction. In the following section, the model developing methodology is explained.
4. Model developing methodology
As mentioned in the introduction, a new approach for model developing is proposed. Since the models will be used in an on-line monitoring system, it is necessary to meet the following requirements:
The models must be developed on physics-based relations, such as thermodynamic and kinematic relations and others.
All models must use the gas path measured parameters as input data.
The structure of the models must be simple.
The measuring error of the gas path parameters, which are the input data of the models, must be taken into account.
The models must have high robustness to the influence of engine’s component deterioration.
Taking into account the main requirements, the following general dependence for any unmeasured parameter is proposed:
Here is the vector of unmeasured parameters to be predicted; is the vector of gas path measured parameters; is the vector of the intermediate unmeasured parameters which describe the thermodynamic properties of the fluid, such as efficiencies and pressure loss factors; and are the ambient conditions.
As shown in Eq. (4), such dependence is not possible to be used in an on-line monitoring system since it includes the vector , which is an unmeasured parameter. In order to solve this inconvenience, it is proposed to estimate each unmeasured parameter as a function
Besides, all the parameters are corrected to standard atmosphere to take into account the influence of atmospheric conditions . After rewriting Eq. (4), the general dependence for any unmeasured parameter is:
Figure 3 shows the algorithm to estimate the unmeasured parameters using the previously presented model developing methodology.
4.1 Model verification
The best models are selected during the model verification process. The total mean square error (MSE) is the main criteria to select the best models; the MSE consists of two components, a truncation error and an instrumental error:
Here is the total MSE, is the truncation error, and is the instrumental error.
4.1.1 Truncation error
The mean square truncation error is:
Here is the value of the unmeasured parameter calculated by the developed models, is the true value obtained from the engine thermodynamic model, and is the sample size; in other words, it is the number of engine operating points considered for analysis corresponding the engine health condition number
The average truncation error in percentage for any engine health conditions is obtained by:
4.1.2 Instrumental error
The MSE for the instrumental error for a healthy engine condition is calculated as follows:
Here is the amount of gas path measured parameters, and is the amount of internal models, which are part of the developed model to estimate the unmeasured parameter.
The average instrumental error in percentage is obtained by:
4.1.3 Model robustness analysis
Engine health conditions in real life are different from engine to engine; therefore, it is necessary to take into account these shifts from the ideal engine. For the model robustness analysis, the truncation error is calculated for several engine health conditions. In  the most common engine faulty conditions of a two-spool free turbine engine were analyzed; as a result, 10 faulty engine conditions were selected.
In Table 2 the 11 engine conditions considered for analysis are listed. The deteriorated engine condition represents a 3% shift from engine health condition.
|Designation||Fault parameter||Deteriorated condition|
|C2||Compressor efficiency decrease|
|C3||Compressor airflow decrease|
|C4||Combustion chamber (CC) efficiency decrease|
|C5||Decrease in the CC total pressure|
|C6||HPT efficiency decrease|
|C7||HPT nozzle box (NB) area increment|
|C8||Decrease in the total pressure between HPT and LPT duct|
|C9||LPT efficiency decrease|
|C10||LPT NB area increment|
|C11||Increment of the air bleed for gas pumping needs|
5. Developing and verification of models for unmeasured parameters for the test case
|Relation of heat transfer coefficients for hot gases|
|Relation of heat transfer coefficients for cooling air|
It is necessary to develop alternative models for each one of the selected thermal boundary conditions. Although the compressor discharge temperature is a measured gas path parameter for our test case (Table 1), it is of particular interest to analyze the effect of its inclusion or exclusion from the list of gas path measured parameters in the overall lifetime prediction.
Since many alternative models were developed, only one example will be shown in order to save available text space; for more details consult .
5.1 Model developing
Let us consider the gas temperature at the inlet of the turbine . As mentioned in Section 4, the models must be physics-based; therefore, we use the relation that describes the power balance between the high-pressure turbine and the high-pressure compressor  as the base equation for model developing:
Here is the turbine power, is the mechanical efficiency, and is the compressor power.
Let us take into account that:
Here and are the gas and air flow consumptions accordingly, and and are the specific heat values at constant pressure for gas and air accordingly.
Solving Eq. (11) for , we obtain:
All the unmeasured parameters in Eq. (14) will be described with the help of the internal model :
Let us remember that all the internal models will be calculated as a polynomial functions using one of the available gas path measured parameters as argument.
Finally, after making the correction to standard atmospheric conditions of Eq. (14), we arrive at the following expression:
Here = 288.15 K is the value of standard atmospheric temperature.
Several models can be developed for the same unmeasured parameter based on different source equations (alternative models). Figure 4 shows the general scheme for the developing of alternative models.
Using the scheme shown in Figure 4, a total of 31 models were developed for our test case (see reference ). A name is given to each developed model for easier identification, for example, the model shown in Eq. (16) is named MTG1. The names and arguments for each alternative developed model are shown in Figure 5.
5.2 Model verification
Let us consider the model MTG1 shown in Eq. (16), which includes the internal model . It is necessary to analyze which of the gas path measured parameters (Table 1) is best suited to be used as argument in the polynomial, as well as the degree of the polynomial that results in the most accurate prediction of .
All of the necessary data for the analysis was obtained using the thermodynamic model of the engine selected as test case . A total of 245 engine operating modes for a healthy engine condition were simulated; these operating modes describe the whole range of the engine operating conditions.
The generated data was randomly divided into two sets. The first set of 123 operating points is used as reference. The second set of 122 operation modes is for model validation. Using the data from the reference set, the coefficients for the polynomial functions were obtained using the least square method.
The polynomial degree was changed from 1 to 4 using each one of the gas path measured parameters (see Table 1) as argument in the polynomial.
Once all the polynomial coefficients describing the internal model were obtained, the value of was calculated. According to the scheme shown in Figure 3, it is necessary to perform an inverse conversion of Eq. (16) to calculate the value of as follows:
The total error (see Eq. (6)) was the main criteria to assess the accuracy of the developed models. A total of 11 engine conditions (Table 2) were considered for the model validation (model robustness analysis).
Figure 6(a) depicts the total error in the prediction of using the model MTG1 with different gas path measured parameters as argument in the polynomial to describe the internal model . From this figure it is clear that the lowest error is obtained when is set as argument.
Figure 6(b) shows that it is sufficient to use a third-degree polynomial as further increment does not reduce the total error in the prediction.
From this analysis the polynomial degree and the gas path measured parameter to be used as argument in Eq. (17) are selected:
The selection of the argument in the
6. Comparative analysis for the model accuracy
Let us conduct a comparative analysis between two approaches for model developing: the first approach for model developing  uses the theory of similarity (reference model), and the second approach is proposed in this chapter and uses a physics-based methodology.
6.1 Thermal boundary condition prediction
The thermal boundary conditions for our test case (see Table 3) were calculated using models developed with both methodologies.
The total error was calculated according to Eq. (6), and the model robustness analysis took into account the 11 engine health conditions listed in Table 2. It is of particular interest to analyze the model robustness, since such analysis for the reference methodology does not exist.
In Figure 8 the truncation errors for the thermal boundary condition prediction are presented.
From Figure 8, it is clear that the models developed using the approach introduced in this chapter are more robust; it means that the models are less sensitive to the deviations from a healthy engine condition. This is a major advantage compared to the reference methodology based in the theory of similarity .
6.2 Prediction of the thermal-stress condition and engine lifetime
The thermal-stress engine condition was calculated using Eqs. (1) and (2). The prediction of the turbine blade lifetime is a very complex process, which involves different factors; however, a conservative lifetime prediction will be enough to assess the impact that a new model developing methodology has on the accuracy of the lifetime prediction. According to the author , a practical way to predict lifetime is the Larson-Miller relation:
As mentioned in Section 5, it is of particular interest to analyze what is the influence of the inclusion or exclusion of the compressor temperature as a gas path measured parameter in the accuracy of TC, SC, and lifetime prediction
6.2.1 Prediction of the thermal-stress condition and engine lifetime when the compressor temperature is not measured
Figure 9 presents the total error in the prediction of TC, SC, and lifetime
From this analysis, it is clear that the methodology used for developing the models of the unmeasured parameters has a great impact in the final accuracy of the lifetime
6.2.2 Prediction of the thermal-stress condition and engine lifetime when the compressor temperature is measured
We repeated the calculation, but this time the value of the compressor temperature is measured. Figure 9(b) shows that the total error in the prediction of TC for both groups is still better when using physics-based models.
Figure 9(d) shows that the accuracy in the prediction of the SC is not significantly affected. From Figure 9(f) it is clear that the improvement in the prediction of TC has a significant impact in the prediction of the lifetime
We can conclude that the accuracy in the prediction of the lifetime is highly improved when the temperature after the compressor is a measured parameter.
A new approach for model developing to estimate the unmeasured parameters in an engine lifetime monitoring system was introduced. This is an effort to increase the accuracy of the lifetime prediction.
All the developed models have a very simple structure and are physics-based, making them ideal to be applied in an on-line lifetime monitoring system.
A turbine blade mounted on the first stage of the high-pressure turbine of a two-spool free turbine power plant is the test case.
Several alternative models were developed using different basic equations. Some of the models include in their structure an internal model, which characterizes the thermodynamic properties of the working fluid, such as efficiencies, pressure loss factors, and others. The internal models were defined by a polynomial function. The best measured parameter used as argument in the polynomial and the degree of the polynomial function were selected using the mean square error as criteria.
All the necessary data for model developing and validation was generated with the engine thermodynamic model.
The truncation and instrumental error are the main criteria to select the best models. Ten engine faulty conditions were considered for the robustness analysis of the models.
A comparative analysis between two model developing methodologies was conducted: physics-based methodology (proposed in this chapter) and models developed on the theory of similarity (reference). The results show that the physics-based models are less sensitive to shifts from the engine healthy condition.
It was found that the use of the proposed model developing methodology provides a better estimation of the thermal boundary conditions, which leads to a significantly better prediction of the lifetime.
It was proven that the compressor temperature has a great impact in the lifetime prediction. If this parameter is not measured, then the accuracy of the lifetime prediction is significantly worse compared to the results obtained when the compressor temperature is measured.
The obtained results show that it is possible to use the proposed model developing methodology in real applications; however, it is necessary to take into account a proper interpretation of the results obtained in this chapter. The reference data, which was used to determine the accuracy of the models, is simulated data; therefore, it is possible that the errors of the lifetime monitoring under real conditions will grow. To avoid such inconvenience, it is possible to replace the data generated with the help of the engine thermodynamic model with real data. This approach is valid, since the engine thermodynamic model is not part of the proposed model developing methodology. In order to obtain the necessary real data, it will be necessary to use additional instrumentation under engine test bed conditions.
|j||j-engine health condition|
|m||value calculated with the help of models, mechanical|
|ref||reference engine mode|
|ST||gas pumping station|
|TT||total mean square error|
|n||rotational speed, number of engine health conditions|
|k||coefficient, isentropic factor|
|S ¯||dimensionless parameter|
|Y||gas path measured parameters|
|W||unmeasured parameters describing thermodynamic properties of the working fluid|
|x||measured parameter, argument of polynomial|
|p 0||standard atmospheric pressure (101.3 KPa)|
|T 0||standard atmospheric temperature (288.15 K)|
|N||sample size (number of engine operation modes), power|
|C||engine condition, coefficient|
|Cp||specific heat at constant pressure|
|Kα||relation of heat transfer coefficient at current and at a reference operation mode|
|α||heat transfer coefficient|
|σ||stress, mean square error, total pressure conservation|
|δ||shift from healthy engine condition|