Prospects for Application of Ship’s Multi-Module Gas Turbine Engines on the Basis of Ceramic Tunnel Turbomachines

Author(s):  
A. V. Sudarev ◽  
A. A. Suryaninov ◽  
V. G. Konakov

Analysis of thermodynamic and thermal-engineering parameters of GTE for mercantile and naval marines was conducted. A conclusion was made that GTEs designed specially for application under sea conditions have the highest efficiency. This is the 36–37% efficiency for simple cycle GTEs. With application of the complex cycle, a notable increase in the engine efficiency could be attained, particularly, by use of structural ceramics (SCMs) on the basis of innovative materials and some novel technological and design concepts. It permits to raise the engine efficiency up to 50% even with the net power of 300–500 kW. Results of numerical calculations for single unit and thirty two module GTEs demonstrated as follows. With the same baseline conditions, a multi-module unit has the volume which is more than twice less and the mass more than five times lower. Though when the number of GTE modules still further increases, decreasing of the turbomachine efficiency becomes a negative factor. To compensate it, it is required to increase the air heater regeneration ratio, to apply helical-channel turbomachines made of heat resistant SCMs, etc. Advantages of multi-module GTEs are evident. Thus, the mean efficiency of a machine during its lifetime increases. The handling independency increases, too. A need in outages to repair machines is eliminated. The control, governing and protection systems become simpler. The fire- and explosion safety increases. In fact, all the designing procedure now reduces to identification of the module number under conditions specified and within a space targeted. As opposed to a conventional ship’s GTE design with the engine having only a single electric net power generator, the multi-module design allows a fast implementation of the entire wide spectrum of operation duties required.

2015 ◽  
Vol 137 (12) ◽  
Author(s):  
Andrew T. Shewhart ◽  
Marc D. Polanka ◽  
Jacob J. Robertson ◽  
Nathan J. Greiner ◽  
James L. Rutledge

The demand for increased thrust, higher engine efficiency, and reduced fuel consumption has increased the turbine inlet temperature and pressure in modern gas turbine engines. The outcome of these higher temperatures and pressures is the potential for unconsumed radical species to enter the turbine. Because modern cooling schemes for turbine blades involve injecting cool, oxygen-rich air adjacent to the surface, the potential for reaction with radicals in the mainstream flow, and augmented heat transfer to the blade arises. This result is contrary to the purpose of film cooling. In this environment, there is a competing desire to consume any free radicals prior to the flow entering the rotor stage while still maintaining surface temperatures below the metal melting temperature. This study evaluated various configurations of multiple cylindrical rows of cooling holes in terms of both heat release and effective downstream cooling. Results were evaluated based on net heat flux reduction (NHFR) and a new wall absorption (WA) parameter which combined the additional heat available from these secondary reactions with the length of the resulting flame to determine which schemes protected the wall more efficiently. Two particular schemes showed promise. The two row upstream configuration reduced the overall augmentation of heat by creating a short, concentrated reaction area. Conversely, the roll forward configuration minimized the local heat flux enhancement by spreading the reaction area over the surface being cooled.


Author(s):  
Andrew T. Shewhart ◽  
Marc D. Polanka ◽  
Jacob J. Robertson ◽  
Nathan J. Greiner ◽  
James L. Rutledge

The demand for increased thrust, higher engine efficiency, and reduced fuel consumption has increased the turbine inlet temperature and pressure in modern gas turbine engines. The outcome of these higher temperatures and pressures is the potential for unconsumed radical species to enter the turbine. Because modern cooling schemes for turbine blades involve injecting cool, oxygen rich air adjacent to the surface, the potential for reaction with radicals in the mainstream flow and augmented heat transfer to the blade arises. This result is contrary to the purpose of film cooling. In this environment there is a competing desire to consume any free radicals prior to the flow entering the rotor stage while still maintaining surface temperatures below the metal melting temperature. This study evaluated various configurations of multiple cylindrical rows of cooling holes in terms of both heat release and effective downstream cooling. Results were evaluated based on a new Wall Absorption parameter which combined the additional heat available from these secondary reactions with the length of the resulting flame to determine which schemes protected the wall more efficiently. Two particular schemes showed promise. The two row upstream configuration reduced the overall augmentation of heat by creating a short, concentrated reaction area. Conversely, the roll forward configuration minimized the local heat flux enhancement by spreading the reaction area over the surface being cooled.


Author(s):  
Kenneth Clark ◽  
Michael Barringer ◽  
Karen Thole ◽  
Carey Clum ◽  
Paul Hiester ◽  
...  

As overall pressure ratios increase in gas turbine engines, both the main gas path and cooling temperatures increase leading to component durability concerns. At the same time effective use of the secondary air for both cooling and sealing becomes increasingly important in terms of engine efficiency. To fully optimize these competing requirements, experiments at engine-relevant conditions are required to validate new designs and computational tools. A test turbine has been commissioned in the Steady Thermal Aero Research Turbine (START) lab. The test turbine was designed to be a 1.5 stage turbine operating under continuous flow simulating engine-relevant conditions including Reynolds and Mach numbers with hardware true to engine scale. The first phase of research conducted using the test turbine, which was configured for a half-stage (vane only), was to study hot gas ingestion through turbine rim seals. This paper presents a series of facility benchmarks as well as validation experiments conducted to study ingestion using a tracer gas to quantify the performance of rim seals and purge flows. Sensitivity studies included concentration levels and sampling flow rates in flow regimes that ranged from stagnant to compressible depending upon the area of interest. The sensitivity studies included a range of purge and leakage flow conditions for several locations in the rim seal and cavity areas. Results indicate reasonable sampling methods were used to achieve isokinetic sampling conditions.


2002 ◽  
Vol 124 (4) ◽  
pp. 1032-1041 ◽  
Author(s):  
J. F. Walton ◽  
H. Hesmat

A review is made of the function of compliant surface bearings in serving the needs of modern turbomachinery. This service extends over a wide spectrum of severe operational and environmental conditions such as extreme low and high temperatures, speeds over 100,000 rpm, and the use of cryogenics as lubricants. The importance of using appropriate simulators that duplicate the actual equipment in evaluating the application of compliant bearings is demonstrated via two specific examples; one, a simulator to evaluate bearings for an air cycle machine and another for an advanced cryogenic device. In view of the known difficulties in using hydrodynamic bearings in vertical machines a new preloaded compliant journal bearing design is offered which performs as well with a vertically mounted shaft as it does in horizontal operation. In terms of the location of the first two rigid-body criticals, the test data show the compliant bearing’s vertical operation to be at most 15 percent lower than for the horizontal case, whereas the maximum vibrational amplitude stayed the same for both modes of operation. This new class of hydrodynamic compliant surface journal bearings now makes possible development of oil-free machines capable of all attitude operation, such as aircraft gas turbine engines undergoing severe pitch maneuvers or machines that must be operated vertically due to space constraints.


Author(s):  
James F. Walton ◽  
Hooshang Heshmat

A review is made of the function of compliant surface bearings in serving the needs of modern turbomachinery. This service extends over a wide spectrum of severe operational and environmental conditions such as extreme low and high temperatures, speeds over 100,000 rpm and the use of cryogenics as lubricants. The importance of using appropriate simulators that duplicate the actual equipment in evaluating the application of compliant bearings is demonstrated via two specific examples; one, a simulator to evaluate bearings for an air cycle machine and another for an advanced cryogenic device. In view of the known difficulties in using hydrodynamic bearings in vertical machines a new preloaded compliant journal bearing design is offered which performs as well with a vertically mounted shaft as it does in horizontal operation. In terms of the location of the first two rigid body criticals the test data show the compliant bearing’s vertical operation to be at most 15% lower than for the horizontal case whereas the maximum vibrational amplitude stayed the same for both modes of operation. This new class of hydrodynamic compliant surface journal bearings now makes possible development of oil-free machines capable of all attitude operation such as aircraft gas turbine engines undergoing severe pitch maneuvers or machines that must be operated vertically due to space constraints.


Author(s):  
M. Ja. Ivanov ◽  
B. I. Mamaev ◽  
R. Z. Nigmatullin

This paper is about the modern mathematical models of working process in the whole flow passage of aviation gas turbine engines. These models are referred as high-level models, based on real 3D geometry of engine flow passage. They allow to simulate steady and unsteady processes in 1D, 2D and 3D formulations, calculate engine performances, determine propagation of radial and circular parameter no uniformities in engine flow passage and predict influence of main parameters on engine efficiency. Typical examples of working process simulation in whole engine and their components are presented below.


1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov

1988 ◽  
Author(s):  
James C. Birdsall ◽  
William J. Davies ◽  
Richard Dixon ◽  
Matthew J. Ivary ◽  
Gary A. Wigell

Alloy Digest ◽  
1997 ◽  
Vol 46 (5) ◽  

Abstract Pyromet CTX-1 is a high-strength, precipitation-hardenable superalloy exhibiting a low coefficient of thermal expansion and high strength up to about 1200 deg F. The alloy possesses high hot hardness and good thermal fatigue resistance. Its applications include components for gas turbine engines, hot-work die applications and high-pressure hydrogen environments. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: FE-56. Producer or source: Carpenter. Originally published February 1976, revised May 1997.


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