Method of Extrapolating Low Speed Compressor Curves Based on Improved 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.

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Development and improvement of compressor performance prognostics for US Navy gas turbine engines

2005 IEEE Aerospace Conference ◽

10.1109/aero.2005.1559650 ◽

2005 ◽

Author(s):

J. Scharschan ◽

D. Caguiat

Keyword(s):

Gas Turbine ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Us Navy ◽

Compressor Performance

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In-Depth Analysis of the Starting Process of Gas Turbine Engines

Proceedings of the National Aerospace Propulsion Conference - Lecture Notes in Mechanical Engineering ◽

10.1007/978-981-15-5039-3_13 ◽

2020 ◽

pp. 219-242

Author(s):

Chinni Jagadish Babu ◽

Mathews P. Samuel ◽

Antonio Davis

Keyword(s):

Gas Turbine ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Depth Analysis ◽

Starting Process

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Dynamics of the starting process of gas turbine engines upon operation of the system in the elastic range

Strength of Materials ◽

10.1007/bf01524273 ◽

1986 ◽

Vol 18 (11) ◽

pp. 1559-1566

Author(s):

Yu. S. Kryuchkov ◽

V. S. Podgurenko ◽

A. I. Tarasenko

Keyword(s):

Gas Turbine ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Elastic Range ◽

Starting Process

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

Volume 2: Turbo Expo 2002, Parts A and B ◽

10.1115/gt2002-30262 ◽

2002 ◽

Cited By ~ 5

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.

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

Volume 3: Turbo Expo 2003 ◽

10.1115/gt2003-38739 ◽

2003 ◽

Cited By ~ 1

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.

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Performance of the Automotive Turbocharger Compressor With Various CO2-Air Mixtures

Volume 8: Microturbines, Turbochargers, and Small Turbomachines; Steam Turbines ◽

10.1115/gt2018-75747 ◽

2018 ◽

Author(s):

Tomasz Duda ◽

Colin Copeland

Keyword(s):

Mass Flow ◽

Pressure Ratio ◽

Test Facility ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Compressor Performance ◽

Speed Parameter ◽

Compressor Map ◽

Gas Recirculation ◽

Measured Pressure

The automotive low pressure exhaust gas recirculation or closed-cycle gas turbine engines are among applications where an alternative fluids to air are used. This paper analyses compressor performance measured while operating with substitute gas. Several compressor performance maps were generated and compared on a steady-state turbocharger test facility run in a closed-loop mode. The automotive centrifugal compressor was mapped with pure air, CO2-air mixtures (3%, 5%, 10% CO2 by mass) and pure CO2. The analysis of the obtained data has indicated that the use of reduced speed parameter and reduced mass flow parameter formulas worked well in the process of the compressor map correction for the CO2-air mixtures. The corrected (with reduced mass flow and speed parameters) compressor performance map generated for the case of pure CO2 has shown a shift in both choke and surge lines and changes in measured pressure ratio and efficiency. Further efficiency and pressure ratio corrections based on the method proposed by Roberts and Sjolander [1] have shown no match between the predicted and measured values of efficiency for CO2. The series of adiabatic 3D CFD simulations indicated that this was likely caused by the heat transfer between the uninsulated turbomachinery components.

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