CCS and Power Systems

Advanced Energy Systems - Hydrogen Turbines


Turbine Thermal Management


Performer: NETL On-Site Research

Project No: FWP-2012.03.02


Accomplishments


FY13

Aerothermal and Heat Transfer:

  • Detailed experimental studies were conducted at the University of Pittsburgh using detached circular pin-fin arrays arranged in a 2-D configuration to demonstrate enhanced heat transfer over smooth cooling channel surfaces. Pin-fin arrays with smaller inter-pin spacing in the span-wise direction were shown to perform as a row of jets which induce high heat transfer at the region immediately behind the pins (Figure 1). Current test data indicate comparable heat transfer enhancement to that of a typical fully-bridged circular pin-fin array.
  • Detailed experimental and numerical studies were conducted on jet impingement channels with staggered and angled jets for NETL-RUA’s near surface embedded micro-channel cooling concept. High heat transfer was observed at the upstream region caused by the impingement effects from the first, second and third jets. The heat transfer at the downstream region decreased substantially as the result of crossflow effects. By staggering and having inclined jets, better mixing and additional vortices result, with an 20% heat transfer enhancement in the channel.
  • Numerical studies using ANSYS CFX were conducted on dimpled and hemispherical protrusion trailing edge zig-zag channel designs. Qualitative comparisons indicated that the zig-zag channels with dimples and hemisperical protrusions have lower heat transfer performance in comparison to the zig-zag channels that contain ribs. The design/configuration of zig-zag channel with dimples and hemisperical protrusions is being revised and further evaluated using ANSYS CFX to down-select the optimized geometry for further experimental testing.
  • Heat transfer and pressure loss testing conducted with a triple impingement trailing edge coupon at near-room temperature indicated that with the presence of 90 º inlet and impingement at the upstream region, the total heat transfer enhancement was 20% higher than previously considered cooling configurations.

Figure 1. Results from Heat Transfer Enhancement Studies Conducted at the University of Pittsburgh for Advanced Internal Airfoil Cooling Concepts.

  • The effects of blowing ratio, density ratio and hole geometry were studied at Virginia Tech to provide a clear understanding of parametric effects on tripod hole film cooling geometries. The 15 º layback antivortex hole design was shown to be an optimal design in terms of overall performance (Figure 2). These designs were tested in a flat plate wind tunnel and on a low speed vane cascade. In all cases, the tripod hole configuration provided over 50% improvement in cooling effectiveness while using 50% less coolant mass even while operating at extremely high blowing ratios of 4.0.
  • Thermal stress distribution analyses were conducted for Haynes 230 coupons containing film cooling tripod holes. Major stress concentrations within the Haynes 230 coupon were not identified, and static thermal gradients are not considered to be an issue for the tripod hole configuration. This effort is being expanded to address similar stress within CM247 tripod hole coupons which will be commercially cast and subsequently tested in NETL’s high temperature, pressurized, aerothermal test facility in Morgantown, WV.

Coatings and Materials Development:

  • Efforts were focused at NETL, CFI, and the University of Pittsburgh on the application of NETL-CFI’s wet slurry diffusion bond coat system on CM247, MarM247, IN939, PM2000, Hayne 230, and Ni-ODS substrates. All coatings consisted of a b-NiAl matrix with distribution of (Cr, Ta, W)-rich precipitates that were dependent on the substrate alloy. Initial isothermal oxidation testing for 100 hours at 1100 ºC led to the formation of an external layer of alumina. The aluminide coating that formed from the slurry on the Fe-based PM2000 alloy from the AID coating-deposition process contained an extensive amount of Kirkendall voids, which detrimentally affected the coating integrity during subsequent thermal exposure.
  • Development of a thin film ODS-layer on channeled nickel-based superalloys at Ames Laboratory was directed to production of NETL-RUA’s near surface embedded micro-cooling channel effort. Ni-ODS powder composition and size fractions were analyzed with respect to oxygen content. Removal of powder particulates 25 μm greatly reduced the oxide content in the resulting coating. Selection of the appropriate deposition process was undertaken to generate dense ODS architectures. HVOF processing was selected for minimal oxidation during deposition while maintaining coating density.

Figure 2. Virginia Tech’s Tripod Hole Film Cooling Configuration, Laboratory Test Equipment and Recent Experimental Results Demonstrating Enhanced Cooling Effectiveness over Current State-of-the-Art Film Cooling Configurations.

  • Efforts were also focused on determining the appropriate processing conditions for application of HVOF Ni-ODS. Reduced temperature combustion conditions were found that generated a dense coating with minimal oxidation. Liquid nitrogen substrate cooling was also effective for reducing oxidation similar to direct HIP’ing. XRD analyses of the heat-treated HVOF coupons confirmed that oxygen-exchange reaction capability of precursor Ni-ODS powders was maintained through thermal spray deposition (Figure 3).
  • A thermoset matrix composite (TSMC) was selected as a viable sacrificial channel filler material for deposition of Ni-ODS on nickel-based superalloys (Figure 4). The filler material consisting of alumina was identified to be ideal for ease of manufacturing, and which withstood both the thermal and mechanical requirements of HVOF. Removal of the TSMC post Ni-ODS deposition via full decomposition was shown to occur at 500-600 ºC.

Figure 3. Microstructure of the Ames University HVOF Ni-ODS Overlay Coating on MarM-247 in the (a) Heat-Treated and (b) As-Sprayed Condition along with Corresponding X-Ray Spectra Indicating the Oxygen-Exchange Reaction and Precipitation of Oxide Dispersion Phase (Y4 Al2O9).

Figure 4. Ames Laboratory Grit Blasted Near Surface Embedded Micro-Channel Concept after Impregnation with Fugitive Thermoset Filler along the External Channels.

Design Integration and Testing:

  • CM247 test coupons containing fully-bridged pin-fin internal cooling arrays, as well as zig-zag trailing edge cooling architectures were successfully cast at Mikro Systems Inc (Figure 5). Computer tomography (CT) scans of the internal configurations at NETL identified the robustness of the TOMO fabrication techniques used by Mikro Systems Inc., for production of complex parts. Similar efforts are underway for production of the first set of CM247 cast coupons containing tripod hole film cooling architectures.
  • Optical pyrometer methods were developed at NETL to measure spatially resolved temperatures on test coupons within NETL’s high temperature, pressurized aerothermal test facility. The accuracy of the optical measurements was determined to be within 8 ºC of thermocouple readings. Additional testing was conducted to characterize incident radiation on the coupons during high temperature exposure. Spatial variation in the incident radiation was characterized which ultimately led to improvement in temperature measurement accuracy.
  • Testing was additionally conducted in NETL’s aerothermal test facility using test coupons with fan-shaped cooling holes over a range of pressures and blowing ratios. The measured overall effectiveness variations with pressure and blowing ratio amounted to engine metal temperature variations of 50 ºC. When compared to testing conducted with a coupon that did not contain cooling holes, locally measured net heat flux reduction was shown to increase with an increase in blowing ratio to a value of 0.5, meaning that fan-shaped film cooling holes could reduce heat flux by 50%. Figure 6 shows the area-average overall effectiveness variation with pressure and blowing ratio for test coupons with fan-shaped film cooling holes.
  • Modifications to the NETL high temperature, pressurized aerothermal test facility included the capability of controlling cooling air temperature. Elevated cooling air temperatures can now be achieved to generate more realistic coolant-to-mainstream density ratios which can be held constant through a range of operating conditions.

Figure 5. Commercial Production of NETL-RUA’s Advanced Cooling Concepts at Mikro Systems Inc. (a) First Cast CM247 Fully Bridged Pin Fin Coupons; (b) CT Scan of Cast CM247 Fully Bridged Pin Fin Coupon Illustrating Absence of Blockage within the Pin Fin Array; (c) CT Scan of Trailing Edge Zig-Zag Cooling Configuration; (d) Tripod Hole Film
Cooling Hole Core.

Figure 6. Area-Average Overall Effectiveness Illustrated as a Function of Blowing Ratio during Testing of Haynes 230 Coupons Containing Fan-Shaped Film Cooling Holes in NETL’s High Temperature, Pressurized Aerothermal Test Facility.

Figure 7. The New Secondary Flow Rotating Rig Design at Penn State has been Completed and Is Currently Being Manufactured and Assembled.

Secondary Flow Rotating Rig:

  • The research team at Penn State officially moved into laboratory rooms and offices of the secondary flow rotating rig facility (Figure 7). Simultaneously, the electrical infrastructure and outdoor substation was completed for supplying power to two 1500 HP compressors.
  • The compressor cooling system, turbine cooling system, dynamometer and water break system, telemetry system, pipe and air flow ductwork system, and magnetic bearing system were procured.
  • Individual part drawings and 3-D solid modeling were completed for all facility and rig parts including all primary and secondary systems. Design reviews of all parts were conducted. The pipe ductwork system was designed in accordance with ASME B31.3-2002 Process Piping - Code for Pressure Piping. An overall facility and rig instrumentation plan was developed. Phase 1 (2014-2015) and Phase 2 (2015 - 2016) test conditions were identified and developed into the design package.
  • Additive manufacturing methods/vendors for turbine vane construction were investigated and used to fabricate the airfoil vanes with integral instrumentation features. Example trial vanes were procured to allow evaluation of the integral instrumentation features. Over sixty Pratt & Whitney cast blades were also procured. A purchase order was issued for turbine disk forging and machining. Manufacturing has begun at multiple vendors on all steel hardware components that comprise the turbine test section.
  • With respect to the pipe ductwork system, request for vendor quotes, competitive bidding, bid awarding, and purchase orders were completed. Manufacturing, plant visit and process reviews were conducted. Outdoor cooling system components were installed. Design and integration of programmable logic control system is in progress. Facility roof penetration locations were identified and prepared/framed. Facility roof platform equipment was acquired. Instrumentation acquisition is in progress (small sensors and large meters). Flow control valves were investigated, vendor bids were obtained, and procurement is in progress. Construction of the two steel chambers located upstream and downstream of the turbine test section is on-going. These chambers serve to condition the pressurized air flow.

Project Details