scholarly journals FT8A, a New High Performance 25 MW Mechanical Drive Aero Derivative Gas Turbine

1990 ◽  
Author(s):  
Aldo Prario ◽  
Heinrich Voss
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Aircraft Engine ◽  
Industrial Applications ◽  
Variable Speed ◽  
Gas Generator ◽  
Low Loss ◽  
Marine Systems ◽  
Collector System ◽  
Power Turbine

This paper describes the FT8A, an advanced state of the art, high performance aeroderivative gas turbine under development for variable speed mechanical drive industrial applications. The gas generator, common to the recently developed FT8, is derived from the Pratt & Whitney JT8D-200 series aircraft engine. The power turbine is being designed and developed by Turbo Power and Marine Systems, Inc. (TPM) and MAN Gutehoffnungshütte AG (MAN GHH) under a joint collaboration program. The power turbine features a three stage rotor simply supported between antifriction bearings, advanced aerodynamics, and a low loss exhaust diffuser/collector system. Design features, performance and typical applications of the FT8A are presented.

FT8: A High Performance Industrial and Marine Gas Turbine Derived From the JT8D Aircraft Engine

1987 ◽  
Author(s):  
William H. Day
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Aircraft Engine ◽  
Industrial Applications ◽  
People’S Republic Of China ◽  
People's Republic Of China ◽  
Unit Order ◽  
Marine Systems ◽  
Republic Of China ◽  
Industrial Gas Turbine

This paper describes the FT8 gas turbine, which has been introduced by Turbo Power and Marine Systems (TPM). The FT8 is derived from the Pratt & Whitney JT8D aircraft engine and the TPM FT4 industrial gas turbine. The FT8 has been launched with a collaboration program between TPM and the China National Aerotechnology Import-Export Corporation (CATIC) of the People’s Republic of China. The collaboration program includes co-production of certain components and a 37-unit order from CATIC over a 10-year period for marine and industrial applications.

Industrial and Marine Development Policy Study and Practices for GT28 Gas Turbine

2017 ◽  
Author(s):  
Xueyou Wen ◽  
Dongming Xiao ◽  
Ningbo Zhao
Keyword(s):  
Gas Turbine ◽  
Development Policy ◽  
High Performance ◽  
Electrical Power ◽  
Operating Performance ◽  
Gas Generator ◽  
Policy Study ◽  
Marine Propulsion ◽  
Power Turbine ◽  
Design Characteristics

As a high performance gas turbine, GT28 combines with a two-spool gas generator and a free power turbine. Under the condition of ISO, its power and efficiency are 28MW and 37% for marine mechanical propulsion, respectively. Considering the design characteristics and operating performance of GT28 gas turbine can meet the requirements of many marine propulsion, mechanical driven and electrical power generation, and this paper introduces the potential application of GT28 gas turbine in different industrial and marine fields. On this basis, the related key technologies are discussed briefly. Finally, a derivative network is presented to describe the relationships of different application and development of GT28 gas turbine.

Mashproekt Scientific and Production Association: A Designer of Gas Turbines for Marine and Industrial Applications

1993 ◽  
Author(s):  
Victor I. Romanov
Keyword(s):  
Soviet Union ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Aircraft Engine ◽  
Industrial Applications ◽  
Production Association ◽  
Technical Documentation ◽  
Power Turbine ◽  
Gear Box ◽  
Propulsion Unit

The first gas turbine unit for Navy application was developed in the Soviet Union in 1950s. It was installed as a boost power unit in a patrol boat and consisted of an aircraft engine rated at about 3000 kW, a free power turbine and a gear box. A successful experience of the unit application permitted to make a decision of establishing a designing organization and production works for marine gas turbine units development and manufacturing in Nikolayev. “Mashproekt” scientific and production association is currently developing technical documentation and prototype engines and units and “Zarya” production association is manufacturing engines in series production. It was planned to develop a gas turbine engine consisting of a two-spool coaxial compressor, a straight-flow combustion chamber, high pressure and low pressure turbines and a free power turbine. Such design meets more fully all-mode operation requirements for a marine propulsion unit. At first simple sycle engines were developed consisting of a gas turbine and a gear box which were used as boost units (CODAG configuration). A significant event was defined with the development of a gas turbine propulsion unit rated at 26 400 kW (13 200 × 2) which consisted of two engines combined through a common gear box (Twin Pac version) (Fig. 1).

Capacity Matching of Aeroderivative Gas Generator With Free Power Turbine: Challenges, Uncertainties, and Opportunities

2019 ◽  
Author(s):  
Deepak Thirumurthy ◽  
Jose Carlos Casado Coca ◽  
Kanishka Suraweera
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Systems Approach ◽  
Gas Generator ◽  
Performance Guarantees ◽  
Design Variables ◽  
Performance Trends ◽  
Power Turbine ◽  
Parameter Matching ◽  
Turbine Capacity

Abstract For gas turbines with free power turbines, the capacity or flow parameter matching is of prime importance. Accurately matched capacity enables the gas turbine to run at its optimum conditions. This ensures maximum component efficiencies, and optimum shaft speeds within mechanical limits. This paper presents the challenges, uncertainties, and opportunities associated with an accurate matching of a generic two-shaft aeroderivative HP-LP gas generator with the free power turbine. Additionally, generic performance trends, uncertainty quantification, and results from the verification program are also discussed. These results are necessary to ensure that the final free power turbine capacity is within the allowable range and hence the product meets the performance guarantees. The sensitivity of free power turbine capacity to various design variables such as the vane throat area, vane trailing edge size, and manufacturing tolerance is presented. In addition, issues that may arise due to not meeting the target capacity are also discussed. To conclude, in addition to design, analysis, and statistical studies, a system-of-systems approach is mandatory to meet the allowed variation in the free power turbine capacity and hence the desired gas turbine performance.

Steam-Cooled Gas Turbine Casings, Struts, and Disks in a Reheat Gas Turbine Combined Cycle: Part I—Compressor and Combustor

1983 ◽  
Vol 105 (4) ◽  
pp. 844-850 ◽  
Author(s):  
I. G. Rice
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Performance ◽  
Material Selection ◽  
Pressure Ratio ◽  
Industrial Applications ◽  
Combined Cycle ◽  
Tip Clearance ◽  
Turbine Output

High-cycle pressure-ratio (38–42) gas turbines being developed for future aircraft and, in turn, industrial applications impose more critical disk and casing cooling and thermal-expansion problems. Additional attention, therefore, is being focused on cooling and the proper selection of materials. Associated blade-tip clearance control of the high-pressure compressor and high-temperature turbine is critical for high performance. This paper relates to the use of extracted steam from a steam turbine as a coolant in a combined cycle to enhance material selection and to control expansion in such a manner that the cooling process increases combined-cycle efficiency, gas turbine output, and steam turbine output.

Development US Navy Gas Turbine Vibration Analysis Expertise: LM2500 Vibration and Trim Balance

2012 ◽  
Author(s):  
Bruce D. Thompson ◽  
Jurie Grobler
Keyword(s):  
Gas Turbine ◽  
Turbine Rotor ◽  
Gas Generator ◽  
Engine Operation ◽  
Engine Design ◽  
Power Turbine ◽  
Us Navy ◽  
Continued Use ◽  
Integrated Performance ◽  
Mean Time

Although generally reliable in-service and with an ever increasing mean time between removal, it was identified in the mid to late 1980’s that the LM2500 gas turbine in US Navy service had a problem with self generated vibration; this was principally due to imbalance in the gas generator or power turbine rotor, however, other non-synchronous sources for vibration were discovered to be important as well. The initial method for resolving this problem was to remove and repair, at a depot, the engines that exceeded the in-service alarm level. This turned out to be a very expensive approach and it was found that most engines that had excessive vibration levels in other respects (performance, etc.) were perfectly acceptable for continued use without repair. Raising the vibration alarm level was tried for a time. However, it became clear that prolonged engine operation with higher levels of vibration were detrimental to the mechanical integrity of the engine. This paper discusses the systematic approach developed to reduce LM2500 self generated vibration levels. This included monitoring system improvements, engine design & hardware improvements and the development and implementation of in-place trim balance. This paper also discusses some of the analysis and practical difficulties encountered reducing and maintaining low LM2500 vibration levels through trim balance and by other means. Also discussed is the present implementation of remotely monitoring LM2500 operating parameters, in particular vibration, through the Integrated Performance Analysis Reports (IPAR) and the Maintenance Engineering Library Server (MELS).

Unbalance Response of a Two Spool Gas Turbine Engine With Squeeze Film Bearings

1981 ◽  
Author(s):  
E. J. Gunter ◽  
D. F. Li ◽  
L. E. Barrett
Keyword(s):  
Gas Turbine ◽  
Nonlinear Effects ◽  
Forced Response ◽  
Squeeze Film ◽  
Gas Generator ◽  
Main Bearing ◽  
Resonant Condition ◽  
Turbine Engine ◽  
Generator Rotor ◽  
Power Turbine

This paper presents a dynamic analysis of a two-spool gas turbine helicopter engine incorporating intershaft rolling element bearings between the gas generator and power turbine rotors. The analysis includes the nonlinear effects of a squeeze film bearing incorporated on the gas generator rotor. The analysis includes critical speeds and forced response of the system and indicates that substantial dynamic loads may be imposed on the intershaft bearings and main bearing supports with an improperly designed squeeze film bearing. A comparison of theoretical and experimental gas generator rotor response is presented illustrating the nonlinear characteristics of the squeeze film bearing. It was found that large intershaft bearing forces may occur even though the engine is not operating at a resonant condition.

Aerodynamic Design of a Power Turbine for an Aircraft Derivative Marine Gas Turbine

1988 ◽  
Vol 110 (1) ◽  
pp. 104-109 ◽  
Author(s):  
Guiming Ji ◽  
Zengxiang Tan ◽  
Mingchang Zhang
Keyword(s):  
Gas Turbine ◽  
Design Methodology ◽  
Aerodynamic Characteristics ◽  
Engineering Practice ◽  
Variable Geometry ◽  
Aerodynamic Design ◽  
Gas Generator ◽  
Power Turbine ◽  
Calculation Results ◽  
Radial Equilibrium

Based on the aerodynamic design and development of a power turbine for an aircraft derivative marine gas turbine in our engineering practice and taking account of the specific features of a marinization effort, this paper describes the design approach and aerodynamic characteristics of the said power turbine, including parameter selection, design methodology, comparison of flow calculation results obtained by simple radial equilibrium and full radial equilibrium method, and a versatile design of the power turbine capable of rendering two power ratings. Also described is the use of variable geometry stator blades to accommodate a small amount of adjustment to the gas generator outlet parameters.

scholarly journals Gas Turbine Compressor Unit Repowering

1996 ◽  
Author(s):  
Joe S. Taylor
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Gas Storage ◽  
Emission Rates ◽  
Gas Generator ◽  
Reciprocating Engine ◽  
Power Turbine ◽  
Macomb County ◽  
The Cost ◽  
Gas Turbine Compressor

This paper presents how a major U.S. gas transmission and storage company restored gas storage peaking capacity by repowering obsolete gas turbine compressor units. Consumers Power Company’s Ray Field located in Macomb County, Michigan, USA, was developed as a 44 BCF working capacity gas storage field in 1966. Due to the high deliverability, the field is operated as a peaking reservoir, handling rates as high as 500 MMCFD on injection and 1,200 MMCFD on withdrawal. Ten (10) 2,750 horsepower gas turbine driven 4-stage centrifugal compressor units were installed in the mid to late 1960’s at the field. The compression is operated 2, 4 and 8 stage, as needed, to cover storage pressures of 450 to 1800 psig. Each centrifugal compressor is driven by a Pratt Whitney (PW) GG-12 Gas Generator firing into a Cooper-Bessemer (CB) RT-27 Power Turbine. By 1980 parts and maintenance services for the PW GG-12 Gas Generator became very expensive to non-existent. Aircraft use of the GG-12 (JT-12) had been phased out. Consumers Power, with 13 of these turbines on their system, was becoming the only remaining user. In the mid 1980’s four (4) of the Ray Field gas turbine compressor units were replaced with two (2) 6,000 horsepower reciprocating engine compressor units. These replacements maintained the deliverability of the field and provided salvageable engines and other parts to maintain the six (6) remaining turbines. However, by 1993 maintenance parts returned as a major problem as well as unit availability on the 6 remaining turbine units. In 1994 Consumers Power committed to a gas turbine unit repowering program as the preferred choice over unit replacement. Two (2) refurbished Solar Centaur T4500 Gas Turbine drives were purchased and installed to repower 2 of the obsolete turbine units. These installations have been very successful. Existing compressors, foundations, piping, coolers and auxiliary systems were re-used with only minor modification. The complete installed cost for repowering was about 33% of the cost experienced for replacement. Installation was completed within eight (8) months of project commitment. The low emission rates from the Solar SoLoNOx Combustors allowed short lead time (6 months) on air emissions permit. New sound attenuation enclosures met the new local noise ordinance and replaced equipment that had been a source of local complaint. PLC based controls improved reliability and flexibility of operation. The additional horsepower available from the T4500 Turbine (4,300 vs 2,750) allows for increased future capacity. Because of the success of the Ray Turbine Repowering Project, Consumers Power has committed to 2 more refurbished Solar Centaur T4500 Units to repower PW/CB Turbines at the St Clair Compressor Station. Solar is scheduled to delivery these 2 units by year-end 1995 for installation in 1996.

scholarly journals A New Turbine for Natural Gas Pipelines

1999 ◽  
Vol 121 (05) ◽  
pp. 72-74
Author(s):  
Jay M. Wilson ◽  
Henry Baumgartner
Keyword(s):  
High Efficiency ◽  
Fuel Efficiency ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Gas Generator ◽  
Natural Gas Pipelines ◽  
Modular Concept ◽  
Power Turbine ◽  
Temperature Capability ◽  
Turbine Design

The new Cooper-Bessemer power turbine is a high-efficiency, center frame-mounted, three-stage unit that can be driven by either the existing RB211-24 gas generator or the new improved version. The upgraded gas generator combined with the new power turbine offers an increase in nominal output from 28.4 MW (38,000 hp) to 31.8 MW (42,600 hp). The new coupled turbine, now being tested, is called the Coberra 6761. Besides improving core engine performance, the program's objectives included improved fuel efficiency and reliability, and easier site serviceability; extension of the modular concept from the gas generator into the power turbine with improvements in sealing, materials, and temperature capability as well as interchangeability of both upgraded turbines with existing hardware. The Rolls-Royce industrial RB211 turbine, derived from an aircraft engine, is the basis for the gas generator end of Cooper Energy Services' Coberra coupled turbines. The power turbine design capacity has a significant effect on the power at a given speed. The flow capacity was optimized to achieve the best thermal efficiency and lower IP speeds to optimize IP compressor efficiency and permit future throttle push.

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