Evaluation of Approaches to Active Compressor Surge Stabilization

1992 ◽  
Author(s):  
J. S. Simon ◽  
L. Valavani ◽  
A. H. Epstein ◽  
E. M. Greitzer
Keyword(s):  
Pressure Rise ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Proof Of Concept ◽  
Control Effectiveness ◽  
Compressor Surge ◽  
Single Sensor ◽  
Compressor Performance ◽  
Definition Of ◽  
Almost All

Recent work has shown that compression systems can be actively stabilized against the instability known as surge, thereby realizing a significant gain in system mass flow range. Ideally, this surge stabilization requires only a single sensor and a single actuator connected by a suitable control law. Almost all research to date has been aimed at proof of concept studies of this technique, using various actuators and sensor combinations. In contrast, the work reported herein can be regarded as a step towards developing active control into a practical technique. In this context, the paper presents the first systematic definition of the influence of sensor and actuator selection on increasing the range of stabilized compressor performance. The results show that proper choice of sensor as well as actuator crucially affects the ability to stabilize these systems, and that, overall, those actuators which are most closely coupled to the compressor (as opposed to the plenum or throttle) appear most effective. In addition, the source of the disturbances driving the system (for example, unsteady compressor pressure rise or unsteady combustor heat release) has a strong influence on control effectiveness, as would be expected for a controls problem of this type. This paper both delineates general methodologies for the evaluation of active compressor stabilization strategies and quantifies the performance of several approaches which might be implemented in gas turbine engines.

Evaluation of Approaches to Active Compressor Surge Stabilization

1993 ◽  
Vol 115 (1) ◽  
pp. 57-67 ◽  
Author(s):  
J. S. Simon ◽  
L. Valavani ◽  
A. H. Epstein ◽  
E. M. Greitzer
Keyword(s):  
Pressure Rise ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Proof Of Concept ◽  
Control Effectiveness ◽  
Compressor Surge ◽  
Single Sensor ◽  
Compressor Performance ◽  
Definition Of ◽  
Almost All

Recent work has shown that compression systems can be actively stabilized against the instability known as surge, thereby realizing a significant gain in system mass flow range. Ideally, this surge stabilization requires only a single sensor and a single actuator connected by a suitable control law. Almost all research to date has been aimed at proof of concept studies of this technique, using various actuators and sensor combinations. In contrast, the work reported here can be regarded as a step toward developing active control into a practical technique. In this context, the paper presents the first systematic definition of the influence of sensor and actuator selection on increasing the range of stabilized compressor performance. The results show that proper choice of sensor as well as actuator crucially affects the ability to stabilize these systems, and that, overall, those actuators most closely coupled to the compressor (as opposed to the plenum or throttle) appear most effective. In addition, the source of the disturbances driving the system (for example, unsteady compressor pressure rise or unsteady combustor heat release) has a strong influence on control effectiveness, as would be expected for a controls problem of this type. This paper both delineates general methodologies for the evaluation of active compressor stabilization strategies and quantifies the performance of several approaches that might be implemented in gas turbine engines.

Method of Extrapolating Low Speed Compressor Curves Based on Improved Similarity Laws

2015 ◽  
Author(s):  
Zhitao Wang ◽  
Yi-Guang Li ◽  
Hui Meng ◽  
Shuying Li ◽  
Ningbo Zhao
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Speed Ratio ◽  
Gas Turbine Engines ◽  
Low Speed ◽  
Compressor Performance ◽  
Starting Process ◽  
Compressor Map ◽  
Similarity Law ◽  
Similarity Laws

Similarity laws for pumps are only applicable to incompressible fluids, and they can’t be directly applied to the extrapolation of compressor characteristic maps. But by varying the exponent of the relative rotational speed ratio to reflect the influence of compressibility, improved similarity laws can be applied to compressors where compressible fluid is considered. This paper proposes a new similarity law for compressor map extrapolation to low speeds by using the two lowest available speed lines and proposes a method of calculating the exponent. A comparison between calculated and real compressor performance of a compressor indicated that this exponent extrapolation method is simple, generic and has acceptable accuracy. The obtained low speed lines of compressors can be applied in gas turbine performance simulations to estimate the starting process of gas turbine engines.

Review—Turbomachinery Performance Deterioration Exposed to Solid Particulates Environment

1984 ◽  
Vol 106 (2) ◽  
pp. 125-134 ◽  
Author(s):  
W. Tabakoff
Keyword(s):  
Gas Flow ◽  
Three Dimensional ◽  
Solid Particles ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Future Design ◽  
Flow Problems ◽  
Performance Deterioration ◽  
Flow Through ◽  
Compressor Performance

The objective of this paper is to review experimental and analytical investigations concerning the effect of the presence of solid particles on the performance of turbomachines. Experimental data on the effect of solid particles on turbine and compressor performance are examined. Some basic data have been reinterpreted to provide guidance for future design. The equations that govern the dynamics of the three-dimensional motion of solid particles suspended in compressible gas flow through a rotating cascade of a turbine are discussed. The results obtained from the solution of these equations are presented to indicate the location on the turbine blade subjected to erosion damage. Some erosion data relevant to gas turbine engines are discussed. The concluding remarks include a global view of the state of the art of particulate flow problems in turbomachinery.

scholarly journals ПАРАМЕТРИЧЕСКАЯ ИДЕНТИФИКАЦИЯ И ОПТИМИЗАЦИЯ ВЫСОКОТЕМПЕРАТУРНЫХ ТЕНЗОРЕЗИСТОРОВ

2020 ◽  
pp. 91-99
Author(s):  
Юрий Алексеевич Гусев
Keyword(s):  
Gas Turbines ◽  
Gas Flow ◽  
Parametric Identification ◽  
Fine Tuning ◽  
Measuring System ◽  
Working Fluid ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Level Lines ◽  
Single Sensor

The development of gas turbine engines (GTE) is inextricably linked with an increase in their main characteristics. In this case, the parameters of the working fluid (in particular, the temperature of the gas flow) and the intensity of loads on the structural elements increase. The strength reliability of highly heated GTE elements is a factor that determines the life of the engine as a whole. The most common cases of damage to GTE elements are caused by static and vibration stresses and mainly relate to the blades of gas turbines operating at temperatures up to 1200оС. Vibration stresses of individual GTE parts can be determined only experimentally during GTE testing and fine-tuning. Their values are determined at individual points of the surfaces of parts by the values of directly measured deformations. At present, the main means for determining the vibration deformations of GTE elements are resistance strain gauges. In the process of testing, the information generated by the strain gages makes it possible to determine not only the dynamic deformation but also the static and dynamic temperature of the blade at the place where the strain gauge is installed. A technique is proposed for the parametric identification of a high-temperature tensoresistor (HTTR), based on the representation of the analyzed HTTR and affecting its state, as some, in the general case, non-linear measuring system. The structural and mathematical models of HTTR are considered, in which both temperature and strain are simultaneously measured using a single sensor element. An original technique is proposed for studying the reliability of the results of HTTR parametric identification. It is proved that the ellipsoidal character of the level lines of residual function, as well as the absence of an extremum region together with the point nature of the minimum, indicate the practical identifiability of the tensometric system. The proposed technique allows a quantitative and qualitative analysis of the effect of shunting on the accuracy of HTTR readings. This technique can also be used to create new types of insulating materials intended for HTTR insulator substrates. This method presents a possibility of the measurement deformation and temperature of element thermal using single platinum-based tensometer sensor.

Lost Thrust Methodology for Gas Turbine Engine Performance Analysis

2005 ◽  
Author(s):  
B. Roth ◽  
J. de Luis
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Engine Performance ◽  
Separate Flow ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Real ◽  
Turbine Performance ◽  
Definition Of

This paper presents and evaluates a lost thrust method for analysis of thermodynamic performance in gas turbine engines. This method is based on the definition of a hypothetical ideal engine that is used as a point of comparison to evaluate performance of the real engine. Specifically, component loss is quantified in terms of decrements in thrust of the real engine relative to the ideal engine having the same design point cycle. These lost thrust decrements provide a basis for accurately evaluating the performance cost of component losses while simultaneously accounting for all component interactions. The analysis algorithm is formally developed in detail and is then demonstrated for a typical separate flow turbofan engine. Various scenarios are examined and the results of these exercises are used to draw conclusions regarding the strengths and weaknesses of this approach to gas turbine performance analysis.

Compressor Fouling Testing on Rolls Royce/Allison 501-K17 and General Electric LM2500 Gas Turbine Engines

2002 ◽  
Author(s):  
Daniel E. Caguiat ◽  
David M. Zipkin ◽  
Jeffrey S. Patterson
Keyword(s):  
Gas Turbine ◽  
Fuel Economy ◽  
Gas Turbines ◽  
Turbine Engines ◽  
Data Sets ◽  
Gas Turbine Engines ◽  
Test Plan ◽  
General Electric ◽  
Compressor Performance ◽  
Naval Surface Warfare

As part of the Gas Turbine Condition Based Maintenance (CBM) Program, Naval Surface Warfare Center, Carderock Division Code 9334 conducted compressor fouling testing on the General Electric LM2500 and Rolls Royce/Allison 501-K Series gas turbines. The objective of these tests was to determine the feasibility of quantifying compressor performance degradation using existing and/or added engine sensors. The end goal of these tests will be to implement an algorithm in the Navy Fleet that will determine the optimum time to detergent crank wash each gas turbine based upon compressor health, fuel economy and other factors which must be determined. Fouling tests were conducted at the Land Based Engineering Site (LBES). For each gas turbine, the test plan that was utilized consisted of injecting a salt solution into the gas turbine inlet, gathering compressor performance and fuel economy data, analyzing the data to verify sensor trends, and assessing the usefulness of each parameter in determining compressor and overall gas turbine health. Based upon data collected during these fouling tests, it seems feasible to accomplish the end goal. Impact Technologies, who analyzed the data sets for both of these fouling tests, has developed a prognostic modeling approach for each of these gas turbines using a combination of the data and probabilistic analysis.

Rolls Royce/Allison 501-K Gas Turbine: Anti-Fouling Compressor Coatings Shipboard — Phase I

2003 ◽  
Author(s):  
Daniel E. Caguiat ◽  
David M. Zipkin ◽  
Jeffrey S. Patterson
Keyword(s):  
Gas Turbine ◽  
United States Navy ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Time Data ◽  
Turbine Generator ◽  
Turbine Engine ◽  
Test Engine ◽  
Compressor Performance ◽  
Naval Surface Warfare

Naval Surface Warfare Center Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 conducted a land-based evaluation of fouling-resistant compressor coatings for the 501-K17 Ship Service Gas Turbine Generator (SSGTG) [1]. The purpose of this evaluation was to determine whether such coatings could be used to decrease the rate of compressor fouling and associated fuel consumption. Based upon favorable results from the land-based evaluation, a similar coated compressor gas turbine engine was installed onboard a United States Navy vessel. Two data acquisition computer (DAC) systems and additional sensors necessary to monitor and compare both the coated test engine and an uncoated control engine were added. The goal of this shipboard evaluation was to verify land-based results in a shipboard environment. Upon completion of the DAC installation, the two gas turbine engines were operated and initial data was stored. Shipboard data was compared to land-based data to verify validity and initial compressor performance. The shipboard evaluation is scheduled for completion in June 2003, at which time data will be analyzed and results published.

Understanding Unsteady Flow Behaviour in a Low Aspect Ratio Contra-Rotating Axial Fan Under Radially Distorted Inflow

2019 ◽  
Author(s):  
Manas Madasseri Payyappalli ◽  
A. M. Pradeep
Keyword(s):  
Aspect Ratio ◽  
Unsteady Flow ◽  
Gas Turbine ◽  
Pressure Sensors ◽  
Pressure Rise ◽  
Wire Mesh ◽  
Turbine Engines ◽  
Length Scale ◽  
Gas Turbine Engines ◽  
Low Aspect Ratio

Abstract Contra-rotation has several advantages like swirl-free discharge, high pressure-rise per stage, and possibility of operating both the rotors at different speeds. With these merits, contra-rotating fan emerges as a competent technology for future gas turbine engines. During operation, gas turbine engines undergo situations like high angle of attack manoeuvres, large cross-winds, bird-hits, etc. which distort the flow at the inlet of the engine. A thorough understanding of the effect of distortion on low aspect ratio contra-rotating fans is missing in literature. This paper reports the consequences of radial distortion on the performance of a low aspect ratio contra-rotating fan. The uniform inlet flow is distorted radially using wire mesh screens. The unsteady data obtained from high response pressure sensors are analysed using Discrete Spatial Fourier Series (DSFS) and Morlet wavelet transform. Both Long Length Scale Disturbances (LLSD) or modal waves and Short Length Scale Disturbances (SLSD) or spikes are observed for different inflow conditions. The stage stalls primarily due to the instabilities arising at the tip region of rotor-1. Rotor-2 shows poor coherence in the disturbances prior to stall compared to that of rotor-1. Tip-distorted flow is dominated with SLSDs in the pre-stall region and hence a stall precursor is not observed whereas clean and hub-distorted flows show prominent LLSDs prior to stall. The radial distortions get redistributed at the exit of rotor-1 and hence, the distorted inflows do not severely lead to instabilities on rotor-2. In summary, this work explains in detail the development of unsteady flow phenomena occurring in a low-aspect ratio contra-rotating fan stage leading to stall and the way in which the system responds to it.

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