Design, Fabrication and Test of a Gas Turbine Engine and Wave Rotor Test Bed PDF Download

Author: John Charles Quackenbush
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 196

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Author: Joshua A. Hartman
Publisher:
ISBN:
Category :
Languages : en
Pages : 143

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With gas turbine engine testing becoming very expensive because of the increasing complexity involved with the engine, engine subsystems, and test support systems, a low-cost Turbine Engine Component Testbed (TECT) is proposed. This engine build is given the designation J1-H-02. In the present study, a small augmented gas turbine engine (GTE) is constructed. The TECT engine is built with modularity as a key design consideration to allow for flame-tube patterns and augmentor sections to be changed quickly for combustion experiments that have gained impetus due to combustion anomalies/instabilities inherent with future military engine augmentors. This testbed allows for an effective way to test new sensors or analytical techniques before full scale testing by allowing an intermediate Technology Readiness Level (TRL) at low-cost and quick schedule turnaround. The TECT was completed using a minor financial investment when matched to comparable capabilities. A data acquisition and control system was developed and tested that allows for real-time engine feedback and control schemes. The components were analyzed for the proper failure modes and performance was predicted using a combination of hand calculations and engine performance prediction software. The compressor performance was predicted using turbomachinery relationships and geometry, then compared with experimental data. The TECT engine was tested across its intended operational envelope at sea-level static (SLS) conditions, with the baseline performance data documented. The applied data reduction approaches were developed and presented.

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722868215
Category :
Languages : en
Pages : 76

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The objective of the program was to determine a wave rotor demonstrator engine concept using the Allison 250 series engine. The results of the NASA LERC wave rotor effort were used as a basis for the wave rotor design. A wave rotor topped gas turbine engine was identified which incorporates five basic requirements of a successful demonstrator engine. Predicted performance maps of the wave rotor cycle were used along with maps of existing gas turbine hardware in a design point study. The effects of wave rotor topping on the engine cycle and the subsequent need to rematch compressor and turbine sections in the topped engine were addressed. Comparison of performance of the resulting engine is made on the basis of wave rotor topped engine versus an appropriate baseline engine using common shaft compressor hardware. The topped engine design clearly demonstrates an impressive improvement in shaft horsepower (+11.4%) and SFC (-22%). Off design part power engine performance for the wave rotor topped engine was similarly improved including that at engine idle conditions. Operation of the engine at off design was closely examined with wave rotor operation at less than design burner outlet temperatures and rotor speeds. Challenges identified in the development of a demonstrator engine are discussed. A preliminary design was made of the demonstrator engine including wave rotor to engine transition ducts. Program cost and schedule for a wave rotor demonstrator engine fabrication and test program were developed. Snyder, Philip H. Glenn Research Center...

Author: T. S. Thurston
Publisher:
ISBN:
Category :
Languages : en
Pages : 41

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This program has produced a production fluidic fuel-control and bleed-air-load-control system which consists of a fuel control, a load valve, and a temperature sensor. Three sets of hardware were produced for use in a follow-on program. This hardware will be subjected to acceptance tests on the AiResearch Model GTCP85-180 gas turbine engine. The production system improved the steady-state performance over that demonstrated on the prototype control produced under the previous program. The fluidic circuits were designed to perform within specification limits when operated at altitude as well as high and low temperature conditions. Designs and drawings were modified wherever necessary to facilitate production. The system underwent engine and fuel bench testing to confirm design improvement and performance. As part of this testing, a 50-hour endurance bench test of the fuel control was performed. This test, as well as the engine tests conducted, identified minor problems with the fuel metering valve and the speed sensor which were easily corrected. The appropriate design changes were incorporated into the production configuration. The production fluidic fuel-control and bleed-air-load-control system performed satisfactorily, meeting the program and engine requirements and is therefore recommended for follow-on program testing. (Author).

Author: Aimee P. Santeler
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 132

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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18

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The U.S. Army Research Laboratory, NASA Glenn Research Center, and Rolls-Royce Allison are working collaboratively to demonstrate the benefits and viability of a wave-rotor-topped gas turbine engine. The self-cooled wave rotor is predicted to increase the engine overall pressure ratio and peak temperature by 300% and 25 to 30%, respectively, providing substantial improvements in engine efficiency and specific power. Such performance improvements would significantly reduce engine emissions and the fuel logistics trails of armed forces. Progress towards a planned demonstration of a wave-rotor-topped Rolls-Royce Allison model 250 engine has included completion of the preliminary design and layout of the engine, the aerodynamic design of the wave rotor component and prediction of its aerodynamic performance characteristics in on- and off-design operation and during transients, and the aerodynamic design of transition ducts between the wave rotor and the high pressure turbine. The topping cycle increases the burner entry temperature and poses a design challenge to be met in the development of the demonstrator engine.

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 10

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The objectives of this report period were to continue the development of the Gas Generator design, to complete the hardware and ancillary hardware fabrication, and commence the Test Preparations for the testing of the non-polluting unique power turbine drive gas generator. Focus during this report period has been on testing the Gas Generator. Because of unacceptable delays encountered in a previously competitively selected test site, CES initiated a re-competition of our testing program and selected an alternate test site. Following that selection, CES used all available resources to make preparations for testing the 10 Mw Gas Generator at the new testing site facilities of NTS at Saugus, CA. A substantial portion of this report period was devoted to Testing Preparations, i.e. test facility development, cold- flow testing, calibration testing, performing igniter ignition testing, and then commencement of the completely assembled Gas Generator Assembly Testing, in process at this writing.

Author: EG-1E Gas Turbine Test Facilities and Equipment
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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This SAE Aerospace Recommended Practice (ARP) is written for individuals associated with the ground-level testing of large and small gas turbine engines and particularly for those who might be interested in constructing new or adding to existing engine test cell facilities.

Author: Arthur F. McLean
Publisher:
ISBN:
Category :
Languages : en
Pages : 232

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A goal of 200 hours of engine of engine rig demonstrations for representative duty cycle temperatures in a regenerated vehicular gas turbine was chosen, with uncooled ceramic components to operate at least 25 hours at 2500 F, considerably beyond the temperatures possible with uncooled metal components. The total systems approach included major efforts in ceramic design, materials development, fabrication process development, and test and evaluation methodology. Considerable progress was made in each of these areas during the course of the program. For example, the strength of reaction bonded silicon nitride (RBSN) used in the stator and rotor blades was more than tripled between July 1971 and July 1977. By the end of the program, 200 hours of duty cycle durability on turbine test rigs (between 1930 F - 2500 F) was attained on RBSN stationary components including stators, nose cones and turbine rotor tip shrouds. Similarly, 200 hours of duty cycling on test rigs was attained with reaction sintered SiC combustors and stators. A 200 hour test of a duo-density silicon nitride rotor with 1800 F rim temperatures, with maximum blade temperatures of approximately 2200 F, was run at speeds to 50,000 rpm. Engine tests of up to 100 hours duration were run with an entire uncooled ceramic stationary flow path (only the rotors being metallic) at up to 87% of engine design speed at 1930 F.A 37 hours engine rig test was run with an uncooled ceramic rotor at temperatures up to 2500 F and speeds up to 50,000 RPM (100% Design E speed).

Author: Arthur F. Mclean
Publisher:
ISBN:
Category :
Languages : en
Pages : 69

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In fiscal year 1977, ERDA joined forces with DARPA to support this project. The progress made on the DARPA Ceramic Turbine Testing Program is presented in this volume while the progress on the ERDA Ceramic Turbine Technology and Ceramic Turbine Materials and NDE Technology Programs is presented in Volume 2. Duo-density rotor fabrication continued with over 600 rotor blade rings injection molded utilizing the automatic solid state control system. Eleven duo-density ceramic turbine rotors were cold spin tested to qualify them for further hot running. Development of the hot spin rigs continued. A combustor flame-out problem and a durability problem with the rotor tip shroud/failure detector were resolved. An important engine test of a duo-density silicon nitride rotor was accomplished. Fabrication development on injection molding of stators and nose cones of 2.7g/cc density was continued on a limited basis. Testing of stationary components continued in both qualification and durability rigs. A complete set of silicon nitride stationary components consisting of a nose cone, two stators, two rotor tip shrouds and a second-stage stator centering ring completed the program objective of 175 hours at 1930 F plus 25 hours at 2500 F with over 40 lights. In addition, a silicon carbide stator successfully completed over 175 hours at 1930 F plus over 28 hours at 2500 F with 52 lights. Stators of two different materials, injection molded silicon nitride and reaction bonded silicon carbide, have now completed the program durability goal of 200 hours.