Combustion liner

For resistance against fatigue, Nimonic 75 has been used with Nimonic 80 and Nimonic 90. Nimonic 75 is an 80-20 nickel-chromium alloy stiffened with a small amount of titanium carbide. Nimonic 75 has excellent oxidation and corrosion resistance at elevated temperatures, a reasonable creep strength, and good fatigue resistance. In addition, it is easy to press, draw, and mold. As firing temperatures have increased in the newer gas turbine models, HA-188, a Cr, Ni-based alloy, has recently been employed in the latter section of some combustion liners for improved creep rupture strength. 

SPE Mashproekt" (2000). The GT 2500 Gas Turbine Engine Fuel Nozzle and Combustion Liner testing on Pyrvac Biofuel. Technical Report, Kiev, Ukraine. 

Pyromet . [Carpenter Tech.] Nickel-base alloy for heat shiel(Is, furnace hardware, gas turbine engine ducting, combustion liners, chemi( l plant hardware, seawater applies. 

The main aspect of design and dimensioning of CMC combustion liners is the integration of CMC components into metallic structures. Therefore the different thermal expansion of the CMC components and the metallic support structure has to be taken into account carefully Based on an anisotropic material model and a failure criterion suitable for the CMC material, Finite Element Analysis supports the design of the liner. 

Hi-Nicalon/Celsian composites are stable up to use temperature of 1100°C in oxidizing environments and degrade at higher temperatures due to the instability of polymer-derived fibers. The stability of Celsian matrix composites may be extended to higher temperatures by more uniform and stable interface coating(s) and by reinforcement with more advanced silicon carbide fiber (Sylramic) for applications as hot components (combustion liner, air foil, nozzle, etc.) in turbine engines. 

Conversion flaps, combustion liners Rocket-nozzle throat sections and exit cones... 

The MS7001FA combustion system consists of 14 combustion chambers with 14-in (36-cm) nominal-diameter combustion liners. Transition pieces conduct the combustion gases to the first-stage nozzle. 

Turbine engine components, combuster liners, blades and vanes SiC, Si3N4, composites. 900-1400 Combustion gases, deposits Na, Mg, Ca sulfates, sodium vanadates Probst(1986)... 

T)q)ical properties for a SiC/SiC CFCC are Young s modulus 100 GPa, tensile strength 260 MPa, and a strain at failure of 0.4%, making it semiductile. Applications include burners, heat exchangers, hot gas fans and filters, and gas turbine combustion liners and shrouds. They have demonstrated 1,000 h without failure as turbine blades in gas turbine engines and 10,000 thermal cycles as radiant burner screens without failure. 

Note, however, that vibration analysis and performance analysis may be linked in many instances. For example, a cracked combustion liner results in a change in TIT and PA calculations. As the cracked metal distxu-hs the airflow and is set into a vibration mode of its own, vibration sensors pick up indication of the cracked hner. Depending on the accuracy of the vibration probes, the sensors may pick up the problem before monitoring of gas path parameters. 

All-oxide CMCs based on alumina fibers and matrices are favorable materials for use at high temperature in oxidizing atmospheres. One possibility for CMCs is the application as combustion liner. As a major drawback oxide fibers show the lowest creep resistance of all ceramic fibers due to their predominant ionic bonds. Therefore, the knowledge of the creep behavior becomes important for construction and dimensioning of components undergoing creep deformation over the life time. 

Flame retardants (qv) are incorporated into the formulations in amounts necessary to satisfy existing requirements. Reactive-type diols, such as A/ A/-bis(2-hydroxyethyl)aminomethylphosphonate (Fyrol 6), are preferred, but nonreactive phosphates (Fyrol CEF, Fyrol PCF) are also used. Often, the necessary results are achieved using mineral fillers, such as alumina trihydrate or melamine. Melamine melts away from the flame and forms both a nonflammable gaseous environment and a molten barrier that helps to isolate the combustible polyurethane foam from the flame. Alumina trihydrate releases water of hydration to cool the flame, forming a noncombustible inorganic protective char at the flame front. Flame-resistant upholstery fabric or liners are also used (27). 

Eunctional or hard chromium plating (169,175) is a successfljl way of protecting a variety of industrial devices from wear and friction. The most important examples are cylinder liners and piston rings for internal combustion engines. Eunctional chromium deposits must be appHed to hard substrates, such as steel, and are appHed in a wide variety of thicknesses ranging from 2.5 to 500 ]Am. 

After combustion, the rich burning mixture leaves the combustion zone and flows between the rows of air jets entering the liner. Each jet entrains air and burning fuel and carries it toward the combustor axis, forming torroidal recirculation patterns around each jet that result in intensive turbulence and mixing throughout the combustor. 

This combustion product is diluted with air entering through holes on the liner to make the temperature appropriate for blade material and to have enough volume-flow in the dilution zone. Air is jet-penetrated mainly because of converging clearances and creates high local pressure. 

Length. Combustor length must be sufficient to provide for flame stabilization, combustion, and mixing with dilution air. The typical value of the length-to-diameter ratio for liners ranges from three to six. Ratios for casing range from two to four. 

VFO works well in gas turbines. In a nine-month test program, the combustion properties of VFO were studied in a combustion test module. A gas turbine was also operated on VFO. The tests were conducted to study the combustion characteristics of VFO, the erosive and corrosive effects of VFO, and the operation of a gas turbine on VFO. The combustion tests were conducted on a combustion test module built from a GE Frame 5 combustion can and liner. The gas turbine tests were conducted on a Ford model 707 industrial gas turbine. Both the combustion module and gas turbine were used in the erosion and corrosion evaluation. The combustion tests showed the VFO to match natural gas in flame patterns, temperature profile, and flame color. The operation of the gas turbine revealed that the gas turbine not only operated well on VFO, but its performance was improved. The turbine inlet temperature was lower at a given output with VFO than with either natural gas or diesel fuel. This phenomenon is due to the increase in exhaust mass flow provided by the addition of steam in the diesel for the vaporization process. Following the tests, a thorough inspection was made of materials in the combustion module and on the gas turbine, which came into contact with the vaporized fuel or with the combustion gas. The inspection revealed no harmful effects on any of the components due to the use of VFO. 

MKI The Mark I containment consists of two separate structures (volumes) connected by a series of l.irae pipes One volume, the dry well, houses the reactor vessel and primary system components. The other i oUmic is a torus, called the wetwell, containing a large amount of water used for pressure suppression and as, i heai sink. The Brunswick units use a reinforced concrete structure with a steel liner. All other M,uk 1 cnni.un ments are free-standing steel structures, The Mark I containments are inerted during plant oper.mon i. prevent hydrogen combustion. 

Liner Formulations For. Polybutadiene Propellants Used In Small Rocket Applications , Report No DREU T.N. 1825/69, (Can) (1969) 7) A.K. Roberts, Preliminary Data On Unstable Combustion In Aluminized Polybutadiene Rocket Motors , Rept No DREU T.N. 1824/69 ... 

Further problems could include damaged or deteriorating flue liners, soot buildup, debris clogging the passageway, and animals or nesting birds could also obstruct the chimney. Oil flues need to be cleaned and inspected annually because deposits of soot may build up on the interior walls of the chimney. Tab. 5.7 gives an overview of possible harmful failures of indoor combustion systems. 

N) E.W. Price, "Recent Advances in Solid Propellant Combustion Instability , Ibid, pp 101-113 O) G.A. Marxman C.E. Wooldridge, "Finite-Amplitude Axial Instability in Solid-Rocket Combustion , Ibid, pp 115-27 P) W.A. Sirignano, "A Theory of Axial-Mode Shock-Wave Oscillations in a Solid-Rocket Combustor ,Ibid, pp 129-37 Q) B.T.Zinn C.T. Saveli, "A Theoretical Study of Three-Dimensional Combustion Instability in Liquid-Propellant Rocket Engines , Ibid, pp 139-47 R) R.J. Priem E.J. Rice, "Combustion Instability with Finite Mach Number Flow and Acoustic Liners , Ibid, pp 149-59 S) M.W. Thring, "Combustion Oscillations in Industrial Combustion Chambers , Ibid, pp 163-68... 

Priem E J. Rice, "Combustion Instability with Finite Mach Number Flow and Acoustic Liners , Ibid, pp 149-59 20) M. Barrere... 

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