Real time performance monitoring of gas turbine engines

• US 4,215,412 A
• Filed: 07/13/1978
• Issued: 07/29/1980
• Est. Priority Date: 07/13/1978
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kamber, Peter W., Bernier, Joseph L.
• Primary Examiner(s): Wise, Edward J.
• Application Number:
  US05/923,950
• Time in Patent Office: 747 Days
• Field of Search: 364/551, 364/572, 364/578, 364/431, 364/119, 364/111, 364/116, 364/105, 364/121, 73/116, 318/563-565, 318/580
• US Class Current: 701/100
• CPC Class Codes: G07C 3/00 Registering or indicating the condition or the working of machines or other apparatus, other than vehicles

Abstract

A real-time gas turbine engine monitoring system is disclosed which includes a digital processor that utilizes a set of scalar coefficients and the current value of various engine operating parameters to predict the current value of a set of engine performance parameters. The actual values of these performance parameters are monitored and compared with the predicted values to supply deviation or error signals to monitoring logic which provides an indication of faults within the digital processor, within the sensor units which provide the actual values of the monitored performance parameters and within the gas turbine engine. In addition, the deviation signals are utilized within the digital processor unit to determine a time dependent quadratic estimate of the temporal characteristics of each monitored engine parameter. Signals representative of this quadratic estimate are supplied to trending logic that provides prognostic information. To adapt the disclosed engine monitoring system to the particular engine being monitored, the system is operable in a calibration mode wherein digital filtering is utilized to automatically determine coefficient values which reflect normal differences in performance between the monitored engine and others of the same type. Since similar digital filtering is utilized in the determination of the temporal characteristics of the monitored engine parameters, common digital processor structure and processing is utilized to effect both system calibration and the estimate of the parameter trends or temporal characteristics.

Claims

1. A system for monitoring at least one performance parameter of a gas turbine engine installation comprising:

first sensor means for supplying a signal representative of the current value of each monitored performance parameter;

second sensor means for supplying a first plurality of signals representative of the current values of an associated plurality of operating parameters of the engine installation being monitored, said plurality of signals being selected so that a signal ##EQU9## provides a current estimate of each monitored performance parameter where y denotes the estimated value of each monitored performance parameter, x_i denotes a series of m independent performance parameters each having a current value dependent on the current value of selected ones of said plurality of signals supplied by said second sensor means and c_i denotes a set of m scalar simulation coefficients;

first signal processing means responsive to said plurality of signals supplied by said second sensor means, said first signal processing means including means for supplying a second plurality of signals representative of the current value of each of said independent performance parameters x_i, means for supplying a third plurality of signals representative of each of said simulation coefficients c_i and means for combining predetermined signals of said second and third plurality of signals to supply a signal representative of the current value of each estimate y of said monitored performance parameters; and

,

second signal processing means responsive to each of said signals representative of the current value of each estimate y of said monitored performance parameters and responsive to each of said signals supplied by said first sensor means for supplying a difference signal representative of the difference between the actual current value of each of said monitored performance parameters and the current estimated value of that same performance parameter.

2. The system of claim 1 further comprising:

selection means selectively operable for switching said system between a performance parameter monitoring mode and a calibration mode; and

coefficient simulation means for supplying each of said scalar simulation coefficients c_i when said selector means is operated to place said system in said calibration mode, said coefficient simulation means including digital filtering means responsive to each difference signal applied by said second signal processing means, said coefficient simulation means being periodically operable to repetitively actuate said digital filtering means and modify each of said simulation coefficients c_i to decrease the difference between said actual value of each monitored performance parameter and said estimated value of that performance parameter with successive operations of said coefficient simulation means.

3. The system of claim 2 further comprising detection means for determining the accuracy of each estimated value of said monitored performance parameter during each periodic operation of said digital filtering means, said detection means including means for indicating that the accuracy of each of said estimated values of said monitored performance parameters is within a predetermined accuracy limit.

4. The system of claim 1 or claim 2 further comprising trending means for supplying a signal representative of the temporal characteristics of at least one of said monitored performance parameters, said trending means responsive to said difference signals supplied by said second signal processing means for estimating the value of a plurality of scalar trending coefficients b_q, q=0, 1, . . . , r, where r and q are predetermined positive real numbers, said coefficients b_q mathematically corresponding to the coefficients of a time dependent polynomial expression ##EQU10## where to denotes the total time said system has operated to monitor each of said performance parameters.

5. The system of claim 4 further comprising steady state detector means responsive to at least one operating parameter of the gas turbine engine installation which includes the gas turbine engine being monitored, said steady state detector means including means for supplying a signal for interrupting the operation of said monitoring system during periods of time in which said gas turbine engine is not being operated in a steady state condition.

6. The system of claim 5 wherein said system monitors at least two engine performance parameters and said system further comprises logic means for logically combining the difference signals supplied by said second signal processing means for supplying a fault indication signal representative of a particular fault within said engine installation and said monitoring system, said system further comprising annunciator means responsive to said fault indication signal for supplying a humanly perceivable indication that said particular fault has occurred.

7. An airborne real time performance monitoring system for periodically monitoring a predetermined plurality of dependent performance parameters y_k, k=1, 2, . . . , n of a gas turbine engine of an aircraft gas turbine engine installation wherein the actual value of each monitored dependent performance parameter is compared with an associated estimated value y_k, K=1, 2, . . . , n to supply a signal indicative of an operating fault in said gas turbine engine, each of said estimated values y_k being determined from a set of m independent performance parameters x_i, i=1, 2, . . . , m which are predetermined functions of selected engine installation operating parameters s_j, j=1, 2, . . . , p where said independent performance parameters x_i collectively characterize the type of gas turbine engine being monitored, and a set of m scalar coefficients c_i, i=1, 2, . . . , m that characterize the particular gas turbine engine being monitored relative to other engines of the same type, m, n and p being predetermined positive real numbers, said gas turbine performance monitoring system comprising:

a plurality of sensor means for supplying signals representative of the value of each of said monitored dependent performance parameters y_k and each of said engine installation operating parameters s_j at each predetermined monitoring time KT where T is a predetermined system sampling interval and K is a positive real integer;

function generating means responsive to said signals supplied by said sensor means for determining the value of each of said independent performance parameters x_i at each monitoring time KT;

digital processing means for determining the value of each of said estimated values y_k at each of said monitoring times KT, said digital processing means including means for setting the value of each y_k numerically equal to ##EQU11## comparator means for determining the difference between the values of each of said dependent performance parameters y_k and the associated estimate y_k at each monitoring time KT, said comparator means including means for supplying a plurality of n difference signals representative of the difference between each of said monitored dependent performance parameters and its associated estimate y_k ; and

logic means responsive to said difference signals supplied by said comparator means for logically combining said difference signals to supply a signal indicative of an operating fault within said gas turbine engine.

8. The performance monitoring system of claim 7 further comprising mode selector means operable for selectively operating said system in a performance parameter monitoring mode and for selectively operating said system in a calibration mode to automatically determine the values of said simulation coefficients c_i which characterize said particular engine being monitored, said digital processor means further including digital filtering means for determining said values of said coefficients c_i, said digital filtering means including:

filter gain means for determining a plurality of m gain factors g_i, i=1, 2, . . . , m for each of said estimated values y_k, k=1, 2, . . . , n at each of said monitoring times KT in which said systems is operated in said calibration mode, each of said gain factors being numerically equal to G_KT =P_K-1)T X_KT (X'"'"'_KT P_K-1)T X_KT +R)^-1 where G is an m element vector including said gain factors associated with said estimated values y_k, X is an m element vector including each of said independent performance parameters x_i that is associated with said particular estimated value y_k, P is a matrix including m rows and m columns of scalar values, R is a predetermined scalar value representative of the system estimation error, the subscripts KT and (K-1)T respectively denote the values of the indicated parameters at the current monitoring time KT and at the nextmost antecedent monitoring time, and X'"'"' denotes the matrix transpose of the vector X;

error covariance means for modifying each of said scalar values of said P matrix to supply scalar values for use as the P.sub.(K-1)T matrix during the nextmost subsequent monitoring time of calibration mode, said modified values of said P matrix mathematically corresponding to P_KT =P.sub.(K-1)(T -G_KT X'"'"'_KT P.sub.(K-1)T ; and

,

coefficient determination means for modifying each set of m simulation coefficients c_i, i=1, 2, . . . , m that is associated with each of said particular simulation values y_k, each set of said modified simulation coefficients mathematically corresponding to C_KT =C.sub.(K-1)T +G_KT (Y_KT -X'"'"'_KT C.sub.(K-1)T), where C is an m element vector including each of said simulation coefficients c_i i=1, 2, . . . , m that are associated with said estimated value y_k.

9. The performance monitoring system of claim 7 or claim 8 wherein said digital processing means further includes trend means for determining the temporal characteristics of each of said monitored dependent performance parameters y_k, k=1, 2, . . . , n, said trend means including means for determining a set of trend coefficients b_q, q=0, 1, . . . , r associated with each of said differences between the actual value of each of said dependent performance parameters y_k, K=1, 2, . . . , n and the estimated value y_k associated with said monitored dependent performance parameter at each monitoring time KT, each of said trend coefficients mathematically corresponding to the expression ##EQU12## where z_k represents the difference between one of said monitored dependent performance parameters y_k and said associated estimate y_k, t represents the total elapsed period of time over which said gas turbine engine has been monitored by said system and r is a predetermined positive read integer.

10. The performance monitoring system of claim 8 wherein said digital processing means includes trend means to adapt saiddigital filter means for determining the temporal characteristics of each of said monitored dependent performance parameters y_k, k=1, 2, . . . , n when said mode selector means is operated to cause said system to operate in said monitoring mode, said trend means including:

means for adapting said filter gain means for the determination of a plurality of gain factors g_i, i=0, 1, . . . , r for each difference z_k, k=1, 2, . . . , m between a monitored dependent performance parameter y_k and the associated estimate y_k of that same performance parameter at each time KT in which said system is operated in said monitoring mode, each gain factor of said plurality of gain factors being numerically equal to G_KT =P.sub.(K-1)T X_KT [X'"'"'_KT P.sub.(K-1)T X_KT +R]^-1 where G is a vector including said gain factors associated with each such said difference z_k, X is a vector including elements t^q, q=0, 1, . . . , r, t being representative of the total time said system has operated in said monitoring mode, P is a matrix including r rows and r columns of scalar values;

means for adapting said error covariance means for modifying each of said scalar values of said P matrix to supply scalar values for use as the P.sub.(K-1)T matrix during the nextmost subsequent monitoring time of said monitoring mode, said modified values of said P matrix mathematically corresponding to P_KT =P.sub.(K-1)T -G_KT X'"'"'_KT P.sub.(K-1)T ; and

means for adapting said coefficient determination means for modifying each set of scalar coefficients b_q, q=0, 1, . . . , r that is associated with each said difference z_k, each set of modified scalar coefficients b_q mathematically corresponding to B_KT =B.sub.(K-1)T +G_KT [Z_KT -X'"'"'_KT B.sub.(K-1)T ] where B denotes a vector including said set of scalar coefficients b_q, q=0, 1, . . . , r associated with said difference z_k.

11. In a gas turbine engine monitoring system of the type including parameter simulation means for estimating the current value of one or more critical engine performance parameters based on the current value of a plurality of operating parameters of the engine installation incorporating the monitored gas turbine engine and means for comparing each estimated current value of a critical performance parameter with the actual current value of that performance parameter to supply an indication of engine malfunction, the improvement comprising digital processing means for supplying the estimated current value of each of said critical performance parameters as scalar values mathematically equal to ##EQU13## where c_i, i=1, 2, . . . , m is a set of predetermined scalar simulation coefficients that is associated with each of said performance parameters with said coefficients c_i collectively characterizing the particular gas turbine engine being monitored relative to other gas turbine engines of the same type, m is a predetermined number and x_i, i=1, 2, . . . , m is a set of predetermined independent engine operating parameters that generically characterize the type of gas turbine engine being monitored, said independent performance parameters being selected from the set of real numbers and the current value of predetermined functions of selected ones of said parameters of said engine installation operating parameters;

said digital processing means including;

means for storing n vectors C_k, k=1, 2, . . . , n, each vector C_k having m scalar coefficient values c_i, i=1, 2, . . . , m, where n denotes the number of critical performance parameters monitored by said system;

means responsive to said current values of said plurality of engine installation operating parameters for determining the current value of each set of predetermined independent performance parameters x_i, i=1, 2, . . . , m;

means for multiplying each independent performance parameter x_i by an associated scalar simulation coefficient c_i ; and

,

means for accumulating the products of each of said multiplications to supply said estimated value of each of said critical performance parameter.

12. The gas turbine engine monitoring system of claim 11 wherein the improvement further comprises mode selection means for selectively operating said system in a monitoring mode to monitor said critical engine performance parameters and selectively operating said system in a calibration mode to automatically determine values of said scalar coefficients c_i that minimize the error between said actual value of each said critical performance parameters and each said estimated current value of that critical performance parameter when said gas turbine engine is functioning normally, said digital processor means being responsive to said mode selector means and further including:

means for storing n sets of filter gain factors G_k, k=1, 2, . . . , n, each set of filter gain factors having m scalar values g_i, i=1, 2, . . . , m, each set of filter gain factors being uniquely associated with the difference between the current value of one of said monitored critical performance parameters and said estimated value of that same critical performance parameter;

means for storing n arrays P_k, k=1, 2, . . . , n each including m x m scalar values, each said array P_k being uniquely associated with one of said difference between the actual current value of said monitored critical performance parameters and the estimated value of that same critical performance parameter;

means for determining the value of each of said filter gain factors g_i, i=1, 2, . . . , m for each of said differences between the current value of one of said monitored critical performance parameters and the estimated value of that same critical performance parameter, including means for establishing each set of filter gain factors G_k to numerically correspond with the matrix expression G_K =P_K X_K [X^T_K P_K X_K +R]^-1 where X is a vector that includes the current value of each of said independent performance parameters, P_K is a m by m matrix corresponding to said stored array P_K, R is a predetermined scalar value representative of the estimation accuracy of said monitoring system and the superscript T denotes the matrix transpose operation;

means for modifying the scalar values stored in said arrays P_k, k=1, 2, . . . , n including means for establishing each said array in accordance with the matrix expression P_k'"'"' =P_k -G_K X^T_K P_k where the matrix P_k'"'"' includes the modified scalar values and the matrix P_k includes said scalar values prior to said modification; and

means for modifying the scalar coefficients stored as each set C_k of scalar coefficients c_i, including means for establishing each set of coefficients C_k in accordance with the matrix expression C_k'"'"' =C_k +G_k [y_i -X^T_k C_k ] where y_i denotes each particular one of the monitored critical performance parameters, the vector C_k'"'"' includes the modified scalar coefficients associated with that monitored critical performance parameter, and the vector C_k includes the scalar coefficient values prior to said modification.

13. The gas turbine engine monitoring system of claim 11 or claim 12 wherein the improvement further comprises trend means for determining the temporal characteristics of each of said monitored critical performance parameters, said trend means including means for determining a set of trend coefficients b_q, q=0, 1, . . . , r for each of said monitored critical performance parameters in accordance with the mathematical expression ##EQU14## where z_k denotes the difference between the current value of each particular value of one of said monitored critical performance parameters and said estimate of that critical performance parameter, t denotes the total time said monitoring system has been operative to monitor said critical performance parameter and r is a preselected positive real number;

and,

logic means responsive to said trend coefficients b_q, q=0, 1, . . . , r for each of said monitored critical performance parameters, said logic means including means for logically combining said trend coefficients to provide an indication of the future operative condition of said monitored gas turbine engine.

14. A method for monitoring the performance of a gas turbine engine comprising the steps of:

(a) detecting the current value of each gas turbine engine performance parameter being monitored;

(b) detecting the current values of a plurality of additional operating parameters of the gas turbine engine being monitored;

(c) generating a set of independent performance parameters x_i, i=1, 2, . . . , m for each of said monitored performance parameters, said independent performance parameters x_i being functionally related to one or more of said detected additional operating parameters of the gas turbine engine being monitored, said independent performance parameters x_i being selected to generically characterize the type of gas turbine engine being monitored;

(d) determining a current estimated value of each of said monitored performance parameters including the steps of determining the mathematical product of each independent performance parameter x_i, i=1, 2, . . . , m multiplied by an associated simulation coefficient c_i, i=1, 2, . . . , m and summing the products over the range i=l to i=m, said simulation coefficients c_i characterizing the particular gas turbine engine being monitored relative to other gas turbine engines of the same type;

(e) determining the difference between each of said monitored performance parameters and the estimated value of that same performance parameter; and

(f) detecting said differences between each of said monitored performance parameters and the estimated value of that same performance parameter to provide an indication of the current condition of said gas turbine engine.

15. The gas turbine engine performance monitoring method of claim 14 further including a calibration step for initially determining scalar values of each of said simulation coefficients that characterize said particular gas turbine engine being monitored relative to other gas turbine engines of the same type, said calibration including the steps of:

(a) determining a plurality of filtered gain coefficients g_i, i=1, 2, . . . , m for each gas turbine engine performance parameter being monitored;

(b) determining the product of each of said differences between a monitored performance parameter and the estimated value of that performance parameter multiplied by each corresponding gain coefficient g;

(c) modifying the current value of each of said simulation coefficients c_i by the value of said product determined in step b; and

(d) repeating steps a, b and c until said difference between each of said monitored performance parameters and said estimated value of that performance parameter is less than a predetermined value.

16. The gas turbine performance monitoring method of claim 15 including the step of prognosticating the future performance of said gas turbine engine, said prognostication including the steps of:

(a) detecting the period of time t said system has been operative to monitor said gas turbine engine performance parameter;

(b) determining a set of scalar coefficients b_q, q=0, 1, . . . , r for each of said differences between a monitored performance parameter and the estimated value of that performance parameter in accordance with the mathematical expression ##EQU15## where z_i denotes one of said differences between a monitored performance parameter and the estimated value of that performance parameter and r is a preselected real positive number;

(c) repeating steps a and b each time said gas turbine engine performance parameter is monitored; and

(d) logically combining said coefficients b_q, q=0, 1, . . . , r to indicate said future performance of said gas turbine engine.