scholarly journals Design Considerations for Ceramic Matrix Composite Vanes for High Pressure Turbine Applications

2013 ◽  
Author(s):  
Robert J. Boyle ◽  
Ankur H. Parikh ◽  
Michael C. Halbig ◽  
Vinod K. Nagpal
Keyword(s):  
High Pressure ◽  
Matrix Composite ◽  
Film Cooling ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Temperature Gradients ◽  
High Pressure Turbine ◽  
Trailing Edge ◽  
Temperature Capability ◽  
Higher Temperature

Issues associated with replacing conventional metallic vanes with Ceramic Matrix Composite(CMC) vanes in the first stage of the High Pressure Turbine(HPT) are explored. CMC materials have higher temperature capability than conventional HPT vanes, and less vane cooling is required. The benefits of less vane coolant are less NOx production and improved vane efficiency. Comparisons between CMC and metal vanes are made at current rotor inlet temperatures and at an vane inlet pressure of 50 atm.. CMC materials have directionally dependent strength characteristics, and vane designs must accommodate these characteristics. The benefits of reduced NOx and improved cycle efficiency obtainable from using CMC vanes. are quantified Results are given for vane shapes made of a two dimensional CMC weave. Stress components due to thermal and pressure loads are shown for all configurations. The effects on stresses of: (1) a rib connecting vane pressure and suction surfaces; (2) variation in wall thickness; and (3) trailing edge region cooling options are discussed. The approach used to obtain vane temperature distributions is discussed. Film cooling and trailing edge ejection were required to avoid excessive vane material temperature gradients. Stresses due to temperature gradients are sometimes compressive in regions where pressure loads result in high tensile stresses.

Ceramic Matrix Composites for High Pressure Turbine Vanes

2014 ◽  
Author(s):  
Robert J. Boyle ◽  
Ankur H. Parikh ◽  
Vinod K. Nagpal ◽  
Michael C. Halbig ◽  
James A. DiCarlo
Keyword(s):  
High Pressure ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Thermal Loads ◽  
Matrix Composites ◽  
Gas Temperature ◽  
High Pressure Turbine ◽  
Trailing Edge ◽  
Barrier Coating

Through thickness, hoop, and spanwise component stresses were calculated for two Ceramic Matrix Composite (CMC) vane configurations. The analyses are for the first stage vane of a High Pressure Turbine. One configuration is for a vane with trailing edge ejection, and the other has no trailing edge ejection. The effects of analyzing separate pressure and thermal loads, as well as combining these loads, are examined. For the case without trailing edge ejection the effects of variations in the stiffness modulus are given. Results are discussed for the midspan region as well as for the entire span. Pressure loads were determined assuming a mainstream gas and coolant pressure of 50 atm. Thermal loads were determined assuming a gas temperature of 2141°K(3394°F), and a maximum Environmental Barrier Coating temperature of 1756°K(2700°F). The desired maximum CMC temperature was 1589°C(2400°F).

Design Considerations for Ceramic Matrix Composite High Pressure Turbine Blades

2019 ◽  
Author(s):  
Robert J. Boyle ◽  
Ankur H. Parikh ◽  
Vinod K. Nagpal
Keyword(s):  
High Pressure ◽  
Matrix Composite ◽  
Turbine Blades ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Aircraft Engine ◽  
Time Frame ◽  
Rotor Blades ◽  
High Pressure Turbine ◽  
Directional Variation

Abstract Issues associated with using SiC/SiC Ceramic Matrix Composite (CMC) materials for High Pressure Turbine (HPT) rotor blades are explored. SiC/SiC materials have higher temperature capability than current HPT superalloys. The strength versus temperature characteristics of SiC/SiC CMCs differs from that of superalloys. Stress analyses were done for a NASA specified notional single aisle aircraft engine blade to be available in the N+3 time frame, (beyond 2030). Stacking, the relative position of hub and tip sections, depends on both pressure and centrifugal forces, and material density. The effect of blade stacking on blade stresses is examined. The change in stresses as the rotation rate varies is examined. The change in engine weight, and thus fuel consumption, due to changes in engine size as the rpm changes is discussed. SiC/SiC CMC materials are generally not isotropic. The effect on stresses and strains of a directional variation in Young’s modulus is examined. Shrouding metallic HPT rotor blades is not common. Shrouding SiC/SiC CMC rotor blades may be feasible due to the lower density, and thus lower centrifugal loads, of SiC/SiC blades. The increase in stresses due to shrouding a SiC/SiC blade is discussed.

Sector Rig Test of a Ceramic Matrix Composite (CMC) Combustor Liner

2006 ◽  
Author(s):  
Venkat Vedula ◽  
Jun Shi ◽  
Shiling Liu ◽  
David Jarmon
Keyword(s):  
Silicon Carbide ◽  
Matrix Composite ◽  
Film Cooling ◽  
Ceramic Matrix Composite ◽  
Network Models ◽  
Ceramic Matrix ◽  
Complete Combustion ◽  
Emissions Modeling ◽  
Component Design ◽  
Temperature Capability

Ceramic Matrix Composite (CMC) combustor liners, due to their high temperature capability, enable the elimination of film cooling present in current metallic liners without increasing the pressure drop in the combustor section of a gas turbine engine. The absence of film cooling and the higher temperature capability of the CMC liner leads to complete combustion of carbon monoxide (CO) close to the combustor walls, resulting in a lower emissions combustor. The benefit of lower CO emissions was predicted through the use of stirred reactor network models in which a series/parallel set of individual perfectly stirred reactors (PSRs) is coupled to simulate a combustor. The paper describes the component design and analysis, emissions modeling, fabrication, and sector rig testing of silicon carbide fiber reinforced silicon carbide matrix (SiC/SiC) combustor liners.

Effect of a Ceramic Matrix Composite Surface on Film Cooling

2021 ◽  
Author(s):  
Peter H. Wilkins ◽  
Stephen P. Lynch ◽  
Karen A. Thole ◽  
San Quach ◽  
Tyler Vincent ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Matrix Composite ◽  
Film Cooling ◽  
Gas Turbines ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Composite Surface ◽  
Minimal Impact ◽  
Cooling Hole ◽  
Adiabatic Effectiveness

Abstract Ceramic matrix composite (CMC) parts create the opportunity for increased turbine entry temperatures within gas turbines. To achieve the highest temperatures possible, film cooling will play an important role in allowing turbine entry temperatures to exceed acceptable surface temperatures for CMC components, just as it does for the current generation of gas turbine components. Film cooling over a CMC surface introduces new challenges including roughness features downstream of the cooling holes and changes to the hole exit due to uneven surface topography. To better understand these impacts, this study presents flowfield and adiabatic effectiveness CFD for a 7-7-7 shaped film cooling hole at two CMC weave orientations. The CMC surface selected is a 5 Harness Satin weave pattern that is examined at two different orientations. To understand the ability of steady RANS to predict flow and convective heat transfer over a CMC surface, the weave surface is initially simulated without film and compared to previous experimental results. The simulation of the weave orientation of 0°, with fewer features projecting into the flow, matches fairly well to the experiment, and demonstrates a minimal impact on film cooling leading to only slightly lower adiabatic effectiveness compared to a smooth surface. However, the simulation of the 90° orientation with a large number of protruding features does not match the experimentally observed surface heat transfer. The additional protruding surface produces degraded film cooling performance at low blowing ratios but is less sensitive to blowing ratio, leading to improved relative performance at higher blowing ratios, particularly in regions far downstream of the hole.

Modeling and Impact of High-pressure Turbine Blade Trailing Edge Film Cooling Hole Variations

2020 ◽  
Author(s):  
Jan Kamenik ◽  
David J. Toal ◽  
Andy Keane ◽  
Lars Högner ◽  
Marcus Meyer ◽  
...  
Keyword(s):  
High Pressure ◽  
Turbine Blade ◽  
Film Cooling ◽  
High Pressure Turbine ◽  
Trailing Edge ◽  
Cooling Hole

scholarly journals Ceramic Matrix Composite Vane Subelement Burst Testing

2006 ◽  
Author(s):  
David N. Brewer ◽  
Michael Verrilli ◽  
Anthony Calomino
Keyword(s):  
High Pressure ◽  
Matrix Composite ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Environmental Barrier ◽  
Environmental Barrier Coating ◽  
Barrier Coating

Burst tests were performed on Ceramic Matrix Composite (CMC) vane specimens, manufactured by two vendors, under the Ultra Efficient Engine Technology (UEET) project. Burst specimens were machined from the ends of 76mm long vane sub-elements blanks and from High Pressure Burner Rig (HPBR) tested specimens. The results of burst tests will be used to compare virgin specimens with specimens that have had an Environmental Barrier Coating (EBC) applied, both HPBR tested and untested, as well as a comparison between vendors.

scholarly journals Preparation of a Ceramic Matrix Composite Made of Hydroxyapatite Nanoparticles and Polylactic Acid by Consolidation of Composite Granules

Nanomaterials ◽  
2020 ◽  
Vol 10 (6) ◽  
pp. 1060
Author(s):  
Elzbieta Pietrzykowska ◽  
Barbara Romelczyk-Baishya ◽  
Jacek Wojnarowicz ◽  
Marina Sokolova ◽  
Karol Szlazak ◽  
...  
Keyword(s):  
Mechanical Properties ◽  
High Pressure ◽  
Polylactic Acid ◽  
Matrix Composite ◽  
Ceramic Matrix Composite ◽  
Ceramic Matrix ◽  
Hybrid Nanocomposites ◽  
Hydroxyapatite Nanoparticles ◽  
Pressure Infiltration ◽  
Composite Granules

Composites made of a biodegradable polymer, e.g., polylactic acid (PLA) and hydroxyapatite nanoparticles (HAP NPs) are promising orthopedic materials. There is a particular need for biodegradable hybrid nanocomposites with strong mechanical properties. However, obtaining such composites is challenging, since nanoparticles tend to agglomerate, and it is difficult to achieve good bonding between the hydrophilic ceramic and the hydrophobic polymer. This paper describes a two-step technology for obtaining a ceramic matrix composite. The first step is the preparation of composite granules. The granules are obtained by infiltration of porous granules of HAP NPs with PLA through high-pressure infiltration. The homogeneous ceramic-polymer granules are 80 μm in diameter, and the composite granules are 80 wt% HAP NPs. The second step is consolidation of the granules using high pressure. This is performed in three variants: Uniaxial pressing with the pressure of up to 1000 MPa at room temperature, warm isostatic compaction (75 MPa at 155 °C), and a combination of the two methods. The combined methods result in the highest densification (99%) and strongest mechanical properties; the compressive strength is 374 MPa. The structure of the ceramic matrix composite is homogeneous. Good adhesion between the inorganic and the organic component is observable using scanning electron microscopy.

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