ChemInform Abstract: TRANSFORMED STEROIDS. 125. SINGLE-STAGE SYNTHESIS OF OXO 16α,17α-CYCLOHEXANOPREGNANES UNDER ATMOSPHERIC AND HIGH PRESSURE

The results of the development of synthesis technique of cyclocarbinol derivatives of cymantrene and the production of relevant barium cyclocarbinolate metal complexes – new, advanced anti-smoke additives were presented. Comparative data on the anti-smoke effectiveness of synthesized compounds and known antismoke additives for diesel fuels were also presented. Established, results of the development of a single-stage synthesis method of cyclocarbinol derivatives of cymantrene can be assumed as a basic process for producing high-effective anti-smoke additives to diesel fuels that comply with the requirements of ecology in operation of diesel vehicles.

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A single-stage full-bridge electronic ballast for high-pressure mercury lamps

2008 SICE Annual Conference ◽

10.1109/sice.2008.4655124 ◽

2008 ◽

Author(s):

Chun-Jen Yao ◽

Huang-Jen Chin ◽

Tai-Hung Wang ◽

Shih-Jen Cheng ◽

Yu-Kang Lo ◽

...

Keyword(s):

High Pressure ◽

Single Stage ◽

Electronic Ballast

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ChemInform Abstract: Single Stage Synthesis of 1,3-Dihydroxy-10-methylacridone.

ChemInform ◽

10.1002/chin.199148164 ◽

2010 ◽

Vol 22 (48) ◽

pp. no-no

Author(s):

J. REISCH ◽

K. SCHMIDT ◽

H. STENKE

Keyword(s):

Single Stage ◽

Stage Synthesis

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Development of New Single and High-Density Heat-Flux Gauges for Unsteady Heat Transfer Measurements for a Rotating Transonic Turbine

Volume 7C: Heat Transfer ◽

10.1115/gt2020-14527 ◽

2020 ◽

Author(s):

Richard Celestina ◽

Spencer Sperling ◽

Louis Christensen ◽

Randall Mathison ◽

Hakan Aksoy ◽

...

Keyword(s):

Heat Transfer ◽

Heat Flux ◽

High Pressure ◽

Pressure Ratio ◽

High Density ◽

Secondary Flows ◽

Single Stage ◽

High Pressure Turbine ◽

Transonic Turbine ◽

New Generation

Abstract This paper presents the development and implementation of a new generation of double-sided heat-flux gauges at The Ohio State University Gas Turbine Laboratory (GTL) along with heat transfer measurements for film-cooled airfoils in a single-stage high-pressure transonic turbine operating at design corrected conditions. Double-sided heat flux gauges are a critical part of turbine cooling studies, and the new generation improves upon the durability and stability of previous designs while also introducing high-density layouts that provide better spatial resolution. These new customizable high-density double-sided heat flux gauges allow for multiple heat transfer measurements in a small geometric area such as immediately downstream of a row of cooling holes on an airfoil. Two high-density designs are utilized: Type A consists of 9 gauges laid out within a 5 mm by 2.6 mm (0.20 inch by 0.10 inch) area on the pressure surface of an airfoil, and Type B consists of 7 gauges located at points of predicted interest on the suction surface. Both individual and high-density heat flux gauges are installed on the blades of a transonic turbine experiment for the second build of the High-Pressure Turbine Innovative Cooling program (HPTIC2). Run in a short duration facility, the single-stage high-pressure turbine operated at design-corrected conditions (matching corrected speed, flow function, and pressure ratio) with forward and aft purge flow and film-cooled blades. Gauges are placed at repeated locations across different cooling schemes in a rainbow rotor configuration. Airfoil film-cooling schemes include round, fan, and advanced shaped cooling holes in addition to uncooled airfoils. Both the pressure and suction surfaces of the airfoils are instrumented at multiple wetted distance locations and percent spans from roughly 10% to 90%. Results from these tests are presented as both time-average values and time-accurate ensemble averages in order to capture unsteady motion and heat transfer distribution created by strong secondary flows and cooling flows.

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ChemInform Abstract: Single-Stage Synthesis of Tetrahydrofuran-3-ol Esters.

ChemInform ◽

10.1002/chin.199921111 ◽

2010 ◽

Vol 30 (21) ◽

pp. no-no

Author(s):

R. F. Talipov ◽

A. M. Gaisin ◽

I. R. Ramazanov ◽

Z. A. Yusupov ◽

M. G. Safarov

Keyword(s):

Single Stage ◽

Stage Synthesis

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Using CFD to Reduce Resonant Stresses on a Single-Stage, High-Pressure Turbine Blade

Volume 4: Turbo Expo 2002, Parts A and B ◽

10.1115/gt2002-30320 ◽

2002 ◽

Cited By ~ 13

Author(s):

J. P. Clark ◽

A. S. Aggarwala ◽

M. A. Velonis ◽

R. E. Gacek ◽

S. S. Magge ◽

...

Keyword(s):

High Pressure ◽

Turbine Blade ◽

Guide Vane ◽

Turbine Blades ◽

Suction Side ◽

Lessons Learned ◽

Single Stage ◽

Navier Stokes ◽

High Pressure Turbine ◽

Time Resolved

The ability to predict levels of unsteady forcing on high-pressure turbine blades is critical to avoid high-cycle fatigue failures. In this study, 3D time-resolved computational fluid dynamics is used within the design cycle to predict accurately the levels of unsteady forcing on a single-stage high-pressure turbine blade. Further, nozzle-guide-vane geometry changes including asymmetric circumferential spacing and suction-side modification are considered and rigorously analyzed to reduce levels of unsteady blade forcing. The latter is ultimately implemented in a development engine, and it is shown successfully to reduce resonant stresses on the blade. This investigation builds upon data that was recently obtained in a full-scale, transonic turbine rig to validate a Reynolds-Averaged Navier-Stokes (RANS) flow solver for the prediction of both the magnitude and phase of unsteady forcing in a single-stage HPT and the lessons learned in that study.

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Design and Test Results of a Ultra High Loaded Single Stage High Pressure Turbine

Volume 6A: Turbomachinery ◽

10.1115/gt2013-94055 ◽

2013 ◽

Cited By ~ 2

Author(s):

Harjit S. Hura ◽

Scott Carson ◽

Rob Saeidi ◽

Hyoun-Woo Shin ◽

Paul Giel

Keyword(s):

High Pressure ◽

Total Pressure ◽

High Speed ◽

Pressure Ratio ◽

Single Stage ◽

Test Results ◽

High Pressure Turbine ◽

Technology Program ◽

High Pressure Ratio ◽

Expected Performance

This paper describes the engine and rig design, and test results of an ultra-highly loaded single stage high pressure turbine. In service aviation single stage HPTs typically operate at a total-to-total pressure ratio of less than 4.0. At higher pressure ratios or energy extraction the nozzle and blade both have regions of supersonic flow and shock structures which, if not mitigated, can result in a large loss in efficiency both in the turbine itself and due to interaction with the downstream component which may be a turbine center frame or a low pressure turbine. Extending the viability of the single stage HPT to higher pressure ratios is attractive as it enables a compact engine with less weight, and lower initial and maintenance costs as compared to a two stage HPT. The present work was performed as part of the NASA UEET (Ultra-Efficient Engine Technology) program from 2002 through 2005. The goal of the program was to design and rig test a cooled single stage HPT with a pressure ratio of 5.5 with an efficiency at least two points higher than the state of the art. Preliminary design tools and a design of experiments approach were used to design the flow path. Stage loading and through-flow were set at appropriate levels based on prior experience on high pressure ratio single stage turbines. Appropriate choices of blade aspect ratio, count, and reaction were made based on comparison with similar HPT designs. A low shock blading design approach was used to minimize the shock strength in the blade during design iterations. CFD calculations were made to assess performance. The HPT aerodynamics and cooling design was replicated and tested in a high speed rig at design point and off-design conditions. The turbine met or exceeded the expected performance level based on both steady state and radial/circumferential traverse data. High frequency dynamic total pressure measurements were made to understand the presence of unsteadiness that persists in the exhaust of a transonic turbine.

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