Marine Spey—SM1A Propulsion Module

1979 ◽  
Vol 101 (1) ◽  
pp. 149-154
Author(s):  
K. G. Page ◽  
C. R. Pack
Keyword(s):  
Corrosion Resistance ◽  
Gas Turbine ◽  
High Efficiency ◽  
Two Stage ◽  
Service Module ◽  
High Shock ◽  
Power Turbine ◽  
Aero Engine ◽  
Shock Resistance ◽  
Engine Components

The requirements for a high efficiency marine gas turbine of 10 to 12 MW output has been identified, particularly for Naval craft. The adaptation and development of a marine version of the Rolls-Royce Spey aero engine has been funded by the Ministry of Defence to meet this requirement. The most suitable version of the aero engine was found to be the TF41 jointly developed by Rolls-Royce and D.D.A. for the L.T.V. Corsair. Redesign involved removal of the bypass portion of the L.P. compressor and the full length bypass duct. Changes to other engine components have also been made to meet the new requirements, together with material changes for improved corrosion resistance. A new two stage free power turbine has been designed to provide long installed life and is not removed with the engine change unit. Particular attention has been given to the mounting system to provide high shock resistance. A full service module is being designed suitable for naval craft, but alternative lightweight installations can be provided.

Performance of a High-Efficiency Radial/Axial Turbine

1987 ◽  
Vol 109 (2) ◽  
pp. 151-154 ◽  
Author(s):  
C. Rodgers ◽  
R. Geiser
Keyword(s):  
Gas Turbine ◽  
Test Performance ◽  
High Efficiency ◽  
Ambient Pressure ◽  
Two Stage ◽  
Axial Turbine ◽  
Turbine Performance ◽  
Exhaust Duct ◽  
Power Turbine ◽  
Isentropic Efficiency

This paper presents the test performance of a lightly loaded, combination radial/axial turbine for a 420-hp, two-shaft gas turbine. This two-stage turbine configuration, which included an interstage duct and an exhaust duct discharging vertically to ambient pressure conditions, was shown to be capable of attaining an overall isentropic efficiency of 89.7 percent. The influence of exhaust diffuser struts on the turbine performance under stalled power turbine conditions was shown to significantly affect compressor and turbine matching.

The New PGT5B/2: A State-of-the-Art 6MW Two-Shaft Gas Turbine

2000 ◽  
Author(s):  
Dino Bianchi ◽  
Paolo Noccioni ◽  
Catherine J. Silvestri
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
High Efficiency ◽  
State Of The Art ◽  
Advanced Technology ◽  
Air Cooling ◽  
Aircraft Engines ◽  
Total Quality ◽  
Two Stage ◽  
Power Turbine

The new PGT5B is a compact, state-of-the-art, 6 MW industrial gas turbine. The unit is available in two configurations: a single shaft for power generation and a two-shaft for mechanical drive applications. Maximum commonality has been maintained between the single and two shaft models. Both units share a common gas generator, with evident benefits in all the installations where mixed operations are required. The two-shaft engine is simply obtained by removing the second stage turbine from the single shaft unit and adding a two-stage power turbine. The unit is an evolution of the existing PGT5, building on the experience of the successful PGT10 model. The synergy between GE Aircraft Engines and GE Power System Nuovo Pignone, with the benefit of GE’s Six Sigma Total Quality Methodology, has permitted the application of the most advanced technology in the development of the major components of the engine. The high efficiency axial compressor is a scaled down version of the successful PGT10B, chosen as the base compressor for the new PGT’s product line. It has been obtained by the combination of advanced fully 3D aero-design, custom airfoil shape and blade stacking optimization. The annular DLE, dual fuel combustion system, developed according to the proven aircraft engines design, is able to satisfy the most stringent environmental regulations. The axial turbine, with sophisticated air cooling system, is designed to reach high values of firing temperature consistent with future uprates. The application of advanced CFD analysis using 3D viscous multi-rows codes and unsteady simulation has resulted in a very high efficiency turbine. The two stage uncooled power turbine capitalizes on Nuovo Pignone’s experience in the mechanical drive market. While the single shaft version is particularly suitable for power generation and cogeneration due to the high exhaust temperature, the two-shaft version, with wide operating speed range, is designed to be a reliable and efficient mechanical drive for compressors and pumps. The Power Turbine speed for optimum application efficiency (up to 34.%) is 12,500 rpm, with a capability range from 50% to 105% of nominal speed. The flexibility of the standard package satisfies the different installation requirements of oil and gas market. The simplicity of construction and the modular design concept of both the engine and package facilitate maintenance and reduce downtime and labor during servicing.

Experimental and Numerical Correlation of Impact of Spherical Projectile for Damage Analysis of Aero Engine Component

2016 ◽  
Vol 66 (2) ◽  
pp. 193 ◽  
Author(s):  
Anuradha Nayak Majila ◽  
Rajeev Jain ◽  
Chandru Fernando D. ◽  
S. Ramachandra
Keyword(s):  
Finite Element ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Metallographic Analysis ◽  
Damage Analysis ◽  
Alloy Plate ◽  
Turbine Engine ◽  
Aero Engine ◽  
Engine Components ◽  
The Impact

<p>Studies the impact response of flat Titanium alloy plate against spherical projectile for damage analysis of aero engine components using experimental and finite element techniques. Compressed gas gun has been used to impart speed to spherical projectile at various impact velocities for damage studies. Crater dimensions (diameter and depth) obtained due to impact have been compared with finite element results using commercially available explicit finite element method code LS-DYNA. Strain hardening, high strain rate and thermal softening effect along with damage parameters have been considered using modified Johnson-Cook material model of LS-DYNA. Metallographic analysis has been performed on the indented specimen. This analysis is useful to study failure analysis of gas turbine engine components subjected to domestic object damage of gas turbine engine. </p><p> </p>

scholarly journals Development and Field Experience of a New 29000 HP Gas Turbine

1980 ◽  
Author(s):  
J. K. Hubbard ◽  
C. Austin
Keyword(s):  
Gas Turbine ◽  
Field Experience ◽  
Performance Test ◽  
High Efficiency ◽  
Test Facility ◽  
Gas Generator ◽  
Initial Field ◽  
Power Turbine ◽  
Exhaust Heat ◽  
Gas Turbine Exhaust

The paper describes the development and initial field experience with a new high efficiency 26,000/30,000 hp gas turbine. Exhaust heat from the power turbine was used to boost the installation thermal efficiency and provide icing protection for the inlet. Wherever possible, proven power turbine design concepts were combined with the advances of a “second generation” aircraft derivative gas generator to produce a reliable machine which was introduced with a minimum of development time. To assure field success, a special test facility was constructed and the unit subjected to a full load mechanical and performance test under simulated field condition.

Operation of Micro Gas Turbine System Employing Two Stage Combustion of Biomass Gas

2009 ◽  
Author(s):  
Yudai Yamasaki ◽  
Yukinori Okada ◽  
Kazuki Iijima ◽  
Shigehiko Kaneko
Keyword(s):  
Gas Turbine ◽  
Pid Controller ◽  
Nox Emission ◽  
Inlet Temperature ◽  
Two Stage ◽  
H Infinity ◽  
Micro Gas Turbine ◽  
Second Stage ◽  
Power Turbine ◽  
System Controller

A two-axis, recuperated cycle micro-gas turbine (MGT) system for biomass gas is developed. The rated specifications of the MGT are as follows, pressure ratio of 2.7, turbine inlet temperature of 1120K, and output power of 5kW. The system consists of three components: the MGT power-generating system, control system and mock biomass gas supply system. The original two-stage combustor and H infinity system controller used in this system are discriminative. Since the gaseous fuel converted from biomass has a low heat quantity, the combustor is designed to achieve both high combustion efficiency and low NOx emission for lower calorific fuel. In the combustor, a stable tubular flame combustion of city gas in the first stage supplies burned gas, which has enthalpy and activated radicals, to the second stage and enables stable ignition and combustion of biomass gas and air premixture. In addition, because the gas composition of biomass gas is also affected by the sources, the gasification method, and the gasifying condition, the system controller is required to absorb fuel fluctuation while meeting the demanded output. Hence, the H infinity algorithm is employed as a system controller because of its robustness against disturbances from the unpredictable fuel component fluctuation. Using this MGT system, an operation test was carried out with mock biomass gases. The rotational speed of the power turbine could be kept almost constant with both mock fermentation gas and pyrolysis gas as the second-stage fuel, and NOx emission was 50ppm when load was increased to a rated power of 5kW. When the second-stage fuel composition changed from 100% methane to 50% methane and 50% CO2 at a certain speed, the power turbine speed could also be kept constant. The H infinity controller is compared with the 2-DOF PID controller for secondary fuel concerning the response to varying load. The former shows slightly better performance than the 2-DOF PID controller.

ALUMINUM C612

Alloy Digest ◽  
1965 ◽  
Vol 14 (9) ◽  
Keyword(s):  
Corrosion Resistance ◽  
Natural Aging ◽  
Heat Treating ◽  
Casting Alloy ◽  
Permanent Mold ◽  
Aluminum Company ◽  
Excellent Corrosion Resistance ◽  
High Shock ◽  
Mold Casting ◽  
Shock Resistance

Abstract Aluminum C612 is a natural aging aluminum permanent mold casting alloy that develops high mechanical properties without a quenching heat treatment. It has high shock resistance and excellent corrosion resistance. It is recommended for highly stressed castings. This datasheet provides information on composition, physical properties, hardness, and tensile properties as well as fatigue. It also includes information on corrosion resistance as well as casting, heat treating, machining, and joining. Filing Code: Al-147. Producer or source: Aluminum Company of America.

ALUMINUM A612

Alloy Digest ◽  
1965 ◽  
Vol 14 (4) ◽  
Keyword(s):  
Mechanical Properties ◽  
Heat Treatment ◽  
Corrosion Resistance ◽  
Aluminum Alloy ◽  
Natural Aging ◽  
Heat Treating ◽  
Aluminum Company ◽  
Excellent Corrosion Resistance ◽  
High Shock ◽  
Shock Resistance

Abstract Aluminum A612 is a natural aging aluminum alloy that develops high mechanical properties without a quenching heat treatment. It has high shock resistance and excellent corrosion resistance. It is recommended for highly stressed castings. This datasheet provides information on composition, physical properties, hardness, tensile properties, and compressive and shear strength as well as fatigue. It also includes information on corrosion resistance as well as casting, heat treating, machining, and joining. Filing Code: Al-144. Producer or source: Aluminum Company of America.

CML-605

Alloy Digest ◽  
1970 ◽  
Vol 19 (1) ◽  
Keyword(s):  
Corrosion Resistance ◽  
Gas Turbine ◽  
Elevated Temperatures ◽  
Base Alloy ◽  
High Strength ◽  
Heat Treating ◽  
Jet Engine ◽  
Cobalt Base Alloy ◽  
Engine Components ◽  
Cobalt Base

Abstract CML-605 is a cobalt-base alloy having high strength, heat and oxidation resistance at elevated temperatures above 1600 F. It is recommended for gas turbine and jet engine components operating in the 1600 to 2000 F temperature range. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: Co-60. Producer or source: Cannon-Muskegon Corporation.

Enhanced Fault Localization Using Probabilistic Fusion With Gas Path Analysis Algorithms

2009 ◽  
Vol 131 (5) ◽  
Author(s):  
A. Kyriazis ◽  
K. Mathioudakis
Keyword(s):  
Path Analysis ◽  
Gas Turbine ◽  
Fault Localization ◽  
Fault Identification ◽  
Diagnostic Problem ◽  
Two Stage ◽  
Precise Location ◽  
Stage Process ◽  
Engine Components ◽  
Probabilistic Fusion

A method for gas turbine fault identification from gas path data, in situations with a limited number of measurements, is presented. The method consists of a two stage process: (a) localization of the component or group of components with a fault and (b) fault identification by determining the precise location and magnitude of component performance deviations. The paper focuses on methods that allow improved localization of the faulty components. Gas path analysis (GPA) algorithms are applied to diagnostic sets comprising different combinations of engine components. The results are used to derive fault probabilities, which are then fused to derive a conclusion as to the location of a fault. Once the set of possible faulty components is determined, a well defined diagnostic problem is formulated and the faulty parameters are determined by means of a suitable algorithm. It is demonstrated that the method has an improved effectiveness when compared with previous GPA based methods.

Development of a Control System for a Dual-Shaft Gas Turbine for Rapid Load Acceptance and Rejection

1962 ◽  
Author(s):  
Leo P. McGuire
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Two Stage ◽  
Control Valves ◽  
Air Inlet ◽  
Voltage Variation ◽  
Power Turbine ◽  
Voltage Recovery

The application required large electrical load changes with very limited variations in frequency and voltage. With a dual-shaft gas turbine, nominal rating 8000 kilowatts, instantaneous loads up to 90 per cent rated were successfully accepted and rejected with frequency maintained within a one and one half per cent band. Voltage variation did not exceed four per cent. Frequency and voltage recovery were well within two seconds. The foregoing was accomplished by incorporating a control system which permitted operation of the turbine at other than normal operating conditions when auxiliary control valves were preset in anticipation of the load variation. The auxiliary control valves were air-inlet throttling valves, an inter-turbine bleed valve, and an additional fuel valve. The basic machine consisted of a 15-stage axial compressor, a two-stage, high-pressure turbine, and a two-stage power turbine. The unique requirements necessitated off-design operation and considerable extrapolation from known test data. However, it was possible to program the control-system components so that a conventional pneumatic control system was capable of maintaining speed within the prescribed band even though the applied load varied from that anticipated by as much as 12.5 per cent.

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