James A. DiCarlo, Nathan S. Jacobson, and Maricela Lizcano

Glenn Research Center, Cleveland, Ohio

Ramakrishna T. Bhatt

Ohio Aerospace Institute, Brook Park, Ohio

Ultra High Temperature (UHT) SiC Fiber (Phase II)

NASA/TM—2015-218883

October 2015
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James A. DiCarlo, Nathan S. Jacobson, and Maricela Lizcano

Glenn Research Center, Cleveland, Ohio

Ramakrishna T. Bhatt

Ohio Aerospace Institute, Brook Park, Ohio

Ultra High Temperature (UHT) SiC Fiber (Phase II)

NASA/TM—2015-218883

October 2015

National Aeronautics and

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Glenn Research Center

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NASA/TM—2015-218883 1 

Ultra High Temperature (UHT) SiC Fiber (Phase II) 

James A. DiCarlo, Nathan S. Jacobson, and Maricela Lizcano 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Ramakrishna T. Bhatt 

Ohio Aerospace Institute 

Brook Park, Ohio 44142 

Background 

Silicon-carbide fiber-reinforced silicon-carbide ceramic matrix composites (SiC/SiC CMC) are 

emerging lightweight structural materials not only for hot section components in gas turbine engines, but 

also for control surfaces and leading edges of reusable hypersonic vehicles as well as for nuclear 

propulsion and reactor components. It has been shown that when these CMC are employed in engine 

hot-section components, the higher the upper use temperature of the SiC fiber and matrix constituents, the 

more performance benefits are accrued, such as higher operating temperatures up to 2700 F, reduced 

component cooling air, reduced fuel consumption, and reduced emissions. The first generation of SiC/SiC 

CMC with a temperature capability of 2200 to 2400 F are on the verge of being introduced into the 

hot-section components of commercial and military gas turbine engines. 

Today the SiC fiber type currently recognized as the world’s best in terms of thermo-mechanical 

performance is the “Sylramic-iBN” fiber. This fiber was previously developed by the Principal 

Investigator at the NASA Glenn Research Center using patented processes (US-7687016) to improve the 

durability of the high-cost commercial “Sylramic” fiber, which in turn was derived from the low-cost 

low-performance commercial Lox-M fiber. Although the Sylramic-iBN fiber shows state-of-the art 

(SOA) creep and rupture resistance for use temperatures up to ~2550 F and is coated with a thin in-situ 

grown boron-nitride (iBN) protective layer, NASA has shown by fundamental creep studies and model 

development that its microstructure and creep resistance could be significantly improved to produce an 

Ultra High Temperature (UHT) SiC fiber. In addition, because the high stiffness of the Sylramic-iBN 

fiber limits its formability into the fiber architectures needed for complex-shaped CMC components, the 

advanced UHT SiC fiber should also seek to reduce this issue.

Purpose of Project 

This Phase II Seedling Fund effort continues Phase I efforts (Ref. 1) focused on the key objective of 

developing a UHT SiC fiber by effectively repeating similar processes used for producing the SylramiciBN fiber and by employing a design of experiments approach to first understand the cause of the less 

than optimum Sylramic-iBN microstructure and then attempting to develop process conditions that 

eliminate or minimize these key microstructural issues. In so doing, it is predicted that that these 

advanced processes could result in an UHT SiC fiber with 20 times more creep resistance than the 

Sylramic-iBN fiber, which in turn would allow SiC/SiC CMC to operate up to 2700 F and above, further 

enhancing the performance benefits of SiC/SiC components in aero-propulsion engines. It is also 

envisioned that the fiber processes developed during Phase II efforts would not only reduce production 

costs for the UHT fiber by combining processes and using low-cost precursor fibers, but also would allow 

the UHT fibers to be directly produced within complex-shaped architectural preforms of the precursor 

fibers, which, because of their lower stiffness, are more amenable to typical textile-forming processes. 
NASA/TM—2015-218883 2 

If successful, the UHT SiC fiber production approach selected for this project is expected to be innovative 

in multiple ways in that 

 It begins with a low-cost, low-grade precursor fiber which is converted by judiciously selected 

high-temperature chemical processes into a state-of-the-art high-performance UHT SiC fiber. The 

fiber temperature capability is projected to be at least 300 °F higher than the Sylramic-iBN fiber. 

 It can be applied to precursor fibers within a variety of textile-formed architectures, which can range 

from continuous lengths of multifiber tows to the complex-shaped architectural preforms needed for 

reinforcement of multidirectionally stressed CMC components. 

 It can be used for a wide range of commercial precursor fiber types with different additives that may 

provide extra beneficial properties to the final UHT fiber. 

 It can be stream-lined with less process steps than currently employed for the best SiC fibers, and thus 

be more cost-effective. 

The UHT fiber approach is also expected to produce high performance fibers with useful properties other 

than greater temperature capability, such as, high thermal conductivity, and with surface coatings that are 

not only environmentally protective, but also compliant enough to provide the weak matrix bonding 

needed for tough CMC.

Approach 

For providing SiC/SiC CMC with structural reliability at high temperatures, polycrystalline SiC fibers 

must meet a variety of property requirements (Ref. 2), the most important of which are high rupture 

strength and high creep resistance. These fibers are thermally stable to well over 3000 °F, but under stress 

will rupture with time at much lower temperatures due to creep and creation of flaws as grains slide over 

one another. Fiber creep and rupture resistance can be improved by increasing grain size, grain size 

uniformity, and viscosity of the grain boundary phases. Currently the state-of-the-art Sylramic-iBN SiC 

fiber is limited in temperature capability to ~2500 °F due to a variety of microstructural issues. Key 

amongst these is the fact that the iBN fiber and its precursor Sylramic fiber typically display a center core 

region where the SiC grains are smaller in size than the grains near the fiber surface, thereby creating a 

shell and core morphology within the fiber cross-section, as shown in Figure 1. Associated with this 

center core is excess carbon and a high density of small voids that remain after final processing. Since 

creep-resistance (and temperature capability) increases with grain size, the shell region provides the 

primary fiber structural capability at high temperatures. Thus as one aspect of the UHT fiber 

development, process conditions are being sought that result in little if any excess creep-prone carbon or 

Figure 1.—Sylramic-iBN SiC fiber 

core-shell morphology with small 

voids (and excess carbon) in the core. 
NASA/TM—2015-218883 3 

volume fraction of voids in the fiber core and a nearly uniform grain size across the fiber diameter so that 

the whole cross-section will be load bearing at high temperatures. Another objective will be to develop 

process conditions that increase the average grain size without significantly debiting fiber strength since 

the grains are effectively flaws in the fiber. Increased grain size will not only increase fiber creep 

resistance, but also increase fiber thermal conductivity, which is important in reducing thermal stresses in 

SiC/SiC CMC components. 

The technical approach selected for this project is to follow process steps similar to those of 

Sylramic-iBN fiber, but apply innovative thermo-chemical treatments at various process stages that result 

in a UHT fiber with larger grain sizes more uniformly distributed in the cross-section, with reduced 

porosity, and with higher viscosity phases in the grain boundaries. The general processing approach 

selected for the UHT fiber is shown in Figure 2. 

First, amorphous commercial precursor SiCO fibers, which contain a high fraction of silicon 

oxycarbide impurity phases, are heat-treated in high-purity argon within Stage 1 furnaces to allow 

gaseous decomposition of the oxide phases leaving pores behind within the fibers. In Phase I, the 

precursor fibers were in straight multifiber tow form; while in Phase II the goal was to look at both 

straight tows and tows woven into complex architectural preforms. Just as in the production of the 

commercial Sylramic fiber (Ref. 3), the porous fibers are then infiltrated with a boron-containing gas to 

form solid boron-containing phases within the fiber pores that act as sintering aids. The boron-doped fiber 

is then exposed to a high sintering temperature where, after the properly selected decomposition and 

infiltration processes, the infused phases are intended to facilitate growth of the fiber grains uniformly 

across the fiber diameter, resulting in the dense and nearly-stoichiometric SiC fiber. Then, as in the 

development of the Sylramic-iBN fiber, since the infused boron-containing phases inhibit fiber creep 

resistance, the sintered fiber is exposed in the Stage 2 furnaces to nitrogen-containing gases that remove 

and alter the creep-prone phases so that the final fiber will not only display increased creep resistance and 

temperature capability, but also a thin protective crystalline BN coating on all fiber surfaces (Ref. 4). A 

key metric for the UHT fiber, shown in Figure 3, is a fiber with higher rupture strength and better 

retention of this strength than the iBN fiber as measured under constant stress in air at 2550 °F. Actual 

upper use temperature for the UHT fiber would depend on the life requirements and stresses within a 

UHT fiber-reinforced CMC component. 

Once UHT fibers are satisfactorily developed by experimental tests on single fibers removed from 

multifiber tows, technical efforts were planned aimed at developing and demonstrating the UHT SiC fiber 

in multiple 2D and 3D architectural preforms that should display thermo-structural capability similar to 

that of the fiber. These preforms will be needed as reinforcement for multidirectionally stressed 

components, such as cooled CMC vanes and blades, but are not easily obtainable with current highperformance high-modulus SiC fibers due to their tendency to fracture when sharply bent to form the 

complex architecture. A final scale-up objective was to seek ways for streamlining the UHT processes 

and for making them as cost-effective as possible. 

Figure 2.—The general process stages selected for producing the UHT SiC fiber. 
NASA/TM—2015-218883 4 

Figure 3.—Metric goal for the UHT SiC fiber: better rupture 

strength and strength retention in air at 2550 °F than the 

state-of-the-art Sylramic-iBN fiber. 

Beyond the technical approaches described above, efforts were planned to demonstrate 

industry-adaptable production methods for the UHT SiC fiber both as continuous multifilament tows and 

as final preforms of CMC components. These efforts will involve collaboration and transfer of the 

developed UHT fiber technologies to select fiber vendors and to CMC end-users to verify enhanced fiber 

performance in commercially-produced SiC/SiC components. For transfer of production methods for 

UHT fiber tows, the infusion process will be faster since we are improving the properties of an existing 

precursor fiber and thus the implementation will not require establishment of a new fiber production line. 

However, it may be more significant and more cost-effective to transfer the processes for UHT fiber 

preforms directly to select CMC vendors, where they perform the UHT preform conversion before 

infiltrating the preforms with matrix material to form the final CMC component. 

Phase II Research 

The primary objective of the Phase II efforts was to continue the fiber development efforts initiated in 

Phase I and described in the Final Phase I report (Ref. 1). During both phases, two types of oxidationcured commercial SiC fibers, the Japanese-produced “Lox-M” and “Nicalon” SiC fibers, were selected as 

the UHT precursor fibers. These fibers are not only low cost and commercially available in large volume, 

but also display low moduli that allows them to be easily woven into complex-shaped fiber preforms 

without fracturing prior to their conversion. 

Experimental Procedure 

As in Phase I, the experimental procedure was to place straight multifiber tows of the precursor fibers 

over a BN boat containing boron-containing powder, and the to process the fibers in a Stage 1 furnace 

under various time-temperature conditions through the steps of (1) gaseous decomposition of their 

silicon-oxycarbide impurity phases, (2) doping with boron-containing gas, and (3) pre-sintering at an 

upper temperature limited by furnace capability. Processed tows were then removed from the Stage 1 

furnace and subjected to final sintering in the Stage 2 one-atmosphere argon furnace at 1800 °C for 1 hr. 

After each process step, microstructures were then characterized for single fibers taken from the tows to 

monitor and understand the physical-chemical changes occurring in the microstructures. If the sintered 

microstructures appeared to show no visible pores in the fiber core, the bend creep, tensile strength, and 

high-temperature rupture-strength of single fibers were then measured using GRC-developed procedures 

and facilities (Ref. 5). If the results of these tests compared well against our creep resistance and tensile 

strength requirements, the sintered fibers would then be subject to high-temperature nitrogen treatments to 

further improve the creep resistance and form an in-situ grown BN coating on the fibers. 
NASA/TM—2015-218883 5 

Figure 4.—Experimental details of the fiber Bend Stress Relaxation (BSR) test. 

For meeting the UHT improved creep-resistance and temperature capability requirements, single 

processed fibers were subjected to the NASA-developed Bend Stress Relaxation (BSR) test to evaluate 

their performance against other SiC fibers (Ref. 6). Figure 4 shows the key details of this test in which the 

processed fiber is bent around a circular graphite mandrel and then heat treated for 1 hr in argon at high 

temperatures. The stress relaxation ratio, m, is defined as the ratio of final to initial stress: 

m =  (t, T, o) / o (t = 0, T, o) = 1 – Ro/Ra. (1) 

As shown in Equation (1), the m value can simply be determined by the radius the fiber is subjected to on 

the mandrel, Ro, and the remaining radius after removal from the mandrel, Ra. If m = 1 (complete spring 

back, Ra = ∞), then the fiber behaves perfectly elastically, i.e., no time-dependent creep deformation. If 

m = 0 (Ro = Ra), then the fibers fully relaxed. Therefore, the higher the value of m for the same time/ 

temperature conditions for a given fiber, the less stress relaxation (more creep resistance) occurred for 

that fiber when compared to another fiber-type. 

The m-ratio results for the processed and sintered fibers were then compared against previous results 

for the Sylramic and Sylramic-iBN fibers to show after each process step whether the converted precursor 

fibers have improved in creep resistance over these two high-performance SiC fibers. For example, 

Figure 5 shows the m-ratio behavior for the Lox-M and Nicalon precursor fibers and how one might 

expect their creep resistance to improve, first to be equivalent to the Sylramic fiber, then the SylramiciBN fiber, and then to be further improved as a UHT fiber. 

It should be mentioned that at the initiation of Phase II, in order to separate and better understand 

process effects during the decomposition and doping steps for both precursor types, a manual linear 

feed-through device shown in Figure 6 was added to the Stage 1 furnace. This allowed movement of the 

boron-containing boat in and out of the furnace hot zone for better control of the boron doping process. 

Also, it was discovered that when only the decomposition step was performed in the original Stage 1 

furnace, boron was deposited on the fibers indicating that boron contamination from previous doping runs 

occurred on the furnace walls in the hot zone area. This issue required the development of a second 

Stage 1 process furnace dedicated to only the decomposition step without the presence of boron. 
NASA/TM—2015-218883 6 

Figure 5.—BSR m-ratio data and goals for the various SiC fiber types 

of this study. 

Figure 6.—New linear feed-through device for better control of 

doping process in the Stage 1 Furnace. 
NASA/TM—2015-218883 7 

Results for Lox-M Precursor 

During Phase I, primary emphasis was placed on conversion of the Lox-M precursor fiber since it is 

also the source of the Sylramic and SOA Sylramic-iBN SiC fibers. As shown in Figure 7, multiple trial 

runs at selected times and temperatures showed that core pores in sintered Lox-M precursor fiber 

originated during decomposition and remained after doping and sintering. Possible mechanisms include a 

high oxycarbide core content leaving pores too large to be sintered and/or residual carbon in the core, 

which is known as a sintering inhibitor for SiC materials. Thus Phase II efforts centered on a more 

detailed study of physical and chemical effects occurring during Lox-M decomposition process. 

To determine the origin of the Lox-M core pores, the new decomposition furnace was used for 

detailed weight loss studies and physical property measurements on the Lox-M fibers after decomposition 

at 1360 °C. This low temperature was chosen to minimize the agglomeration of any excess carbon in the 

fiber core that occurs during higher temperature decomposition conditions (Ref. 7). Fiber physical 

measurements after decomposition of the Lox-M precursor fiber at 1360 °C are shown in Table 1. The 

length and diameter shrinkage as well as loss in tensile strength are to be expected due to the void 

creation by decomposition of the silicon-oxycarbide impurity phases in the original Lox-M fiber. 

However, the weight loss of ~25 percent for complete decomposition of our current Lox-M fibers 

indicates an impurity oxygen content of ~13 percent, which is larger than that indicated in the 

Dow Corning patent of 11 percent for their highest quality Sylramic fibers (Ref. 3). 

Figure 7.—Microstructures of treated Lox-M fibers showing retention of decomposition pores. 

TABLE 1.—PHYSICAL MEASUREMENTS AFTER DECOMPOSITION 

OF THE LOX-M PRECURSOR FIBER AT 1360 °C 

 
NASA/TM—2015-218883 8 

Figure 8.—Microstructure of fully decomposed Lox-M fibers showing large core pores that not only 

result in low fiber strength, but also are difficult to remove during the subsequent sintering process. 

Also, after complete decomposition of our Lox-M fibers for 12 or greater hours at 1360 °C, 

microstructures of the decomposed fibers showed exceptionally large pores in the fiber cores as indicated 

in Figure 8. From these observations, it is currently concluded at the end of Phase II that: (1) the pores left 

by decomposition were probably too large to be eliminated during final sintering, an issue that goes back 

to amount of oxycarbide impurity introduced in original processing of our Lox-M fibers, and (2) for any 

future Lox-M studies, we need to use Lox-M fibers with lower oxygen and weight loss, which then 

should be expected to yield smaller and hopefully more sinterable core pores.

Results for Nicalon Precursor 

In continued studies between Phase I and II, it was determined that under optimized process 

conditions, uniform microstructures with no obvious pores were observed in the treated Nicalon precursor 

fiber after sintering. These encouraging results, which are shown in Figure 9, resulted in a Phase II 

proposal and award. Thus in Phase II, those sintered Nicalon fibers with uniform microstructures were 

subjected to creep, tensile strength, and chemical analyses to check their quality for further processing 

into a UHT SiC fiber. 

For creep analysis, the Bend Stress Relaxation (BSR) test was applied to single sintered Nicalon 

fibers with uniform microstructures. The m-ratio results shown in Figure 10 show that sintered Nicalon 

fibers with uniform microstructures display creep behavior equal to that of the Sylramic fibers, indicating 

in-house processes can successfully produce fibers with improved grain structure, which in turn should 

then be convertible to iBN-type fibers. 

For tensile strength analysis, single sintered Nicalon fibers with uniform microstructures were then 

subject to room-temperature tests at 1-in. gauge length. Average strengths were found to be lower than 

those of the commercial Sylramic fibers (~1.5 vs ~3 GPa). As shown in Figure 11, reduced strength for 

the sintered Nicalon fiber is currently attributed to tiny kinks along its length as well as surface cracks, 

which have not been observed in the sintered Lox-M fibers. One possible mechanism for the kinks and 

cracks is that as the fiber sintered and contracted in volume, this volume change was non-uniform within 

the fiber causing local kinking and associated residual stresses that resulted in surface cracking. Trapped 

oxy-carbide phase in the fiber core may also have resulted in residual stresses. This kinking issue has also 

been noted in the literature for sintered SiC fibers and has been solved by applying a slight tension to the 

fibers during any shrinkage process (Ref. 8), a solution yet to be attempted. 
NASA/TM—2015-218883 9 

Figure 9.—Microstructure of treated and sintered Nicalon fibers showing that certain process 

conditions can produce near-uniformity and reduced void content across the fiber cross-section. 

Figure 10.—BSR m-ratio data for treated and sintered Nicalon 

fibers with near-uniform microstructures showing creep 

resistance equivalent to the commercial Sylramic fiber. 

Figure 11.—Strength-limiting surface crack 

for treated and sintered Nicalon fiber 

with near-uniform microstructure. 
NASA/TM—2015-218883 10 

To better understand any chemical sources for the fiber surface cracks, microprobe measurements 

were made at the end of Phase II in order to identify the chemical elements across the sintered Nicalon 

fiber diameter. The results are shown in Figure 12. From these observations, it is currently concluded that 

(1) the deox time-temperature conditions for the converted Nicalon fibers, even with apparently uniform 

microstructures, were not sufficient to completely remove the oxy-carbide phase in the fiber core, and (2) 

for any continued Nicalon precursor studies, we should be seeking improved process conditions that 

result in full decomposition and improved removal of carbon within the fiber core, as well as providing 

tension on the Nicalon fibers during all process stages during which fiber shrinkage occurs. 

For future studies, in order to address the need for tension on the fibers during shrinkage, two new 

holders for precursor fiber tows have been developed (Fig. 13) where the tows are clamped or wound in 

grooves around graphite blocks, which because of their stable size, serve to apply tension to the fibers as 

they sinter and contract during the high-temperature process steps. 

Figure 12.—Treated and sintered Nicalon fibers with near-uniform microstructures still retain the silicon-oxycarbide 

impurity in their core region. 

Figure 13.—New specimen holders for precursor fiber tows designed to apply tension to Nicalon precursors during 

fiber shrinkage stages. 

 
NASA/TM—2015-218883 11 

Summary of Phase II Accomplishments 

 Although time consuming, significant progress was made at NASA Glenn in developing the proper 

process equipment, safety permits, specimen preparation methods, characterization techniques, and 

property tests for producing and validating a UHT SiC fiber for SiC/SiC CMC. 

 Task efforts verified that the Glenn UHT fiber process methods and facilities can indeed convert the 

impure microstructures of low-cost highly-available SiC fibers into microstructures equivalent to or 

better than those of the high-cost low-availability Sylramic SiC fiber. Using NASA’s nitrogen 

processes, these fibers should be directly convertible into fibers with creep behavior similar or better 

than that of the current SOA Sylramic-iBN fiber. 

 This result implies that as further studies increase the strength of the converted fibers, processes will 

be available within NASA and industry for producing fibers similar to the Sylramic-iBN fibers not 

only within tows, but more importantly within 2D and 3D complex-shaped preforms of CMC 

components, an important technical result not available today. 

 Although complete success has not yet been achieved in completely eliminating issues in the 

converted fiber cores, lessons were learned, and feasible approaches for eliminating these issues will 

be studied under the NASA Transformational Tools and Technologies Project in order to meet one of 

its key technical challenges of a 2700 °F CMC turbine engine component. 

Current TRL 

Innovation has moved from basic principles (TRL1) to formulated concept (TRL2). 

Applicable NASA Programs/Projects 

In terms of NASA significance, the UHT fiber addresses aeronautics challenges within the NASA 

Transformational Tools and Technologies Project, such as minimally and un-cooled SiC/SiC propulsion 

components that will require temperatures on the order of 2700 °F. Similar goals also exist for the new 

Air Force multimillion dollar program aimed at developing 2700 °F SiC/SiC engine materials. 

Publications and Patent Applications 

When project is fully successful, patent applications are expected concerning the processing of SiC 

fibers with state-of-the-art thermal-structural capability and also concerning the low-cost processing of 

these fibers in the complex architectural preforms needed for aerospace components.

Awards and Honors Related to Seedling Research 

To be determined

Seedling Related NASA Publication 

J.A. DiCarlo: Modeling Creep of SiC Fibers and Its Effects on High Temperature SiC/SiC CMC. 

Proceedings of 38th Annual Conference on Composites, Materials, and Structures, January 2014, 

Cape Canaveral, Florida. 

 
NASA/TM—2015-218883 12 

References 

1. J. DiCarlo, M. Lizcano, N. Jacobson, and R. Bhatt: Ultra High Temperature (UHT) SiC Fiber 

(Phase I), NASA/TM—2012-217751, 2012. 

2. J. DiCarlo: SiC Fiber Technology Status. Presentation at Air Force SiC Fiber Forum, Dayton, Ohio, 

Dec. 15, 2009. 

3. US Patent 5366943: Polycrystalline SiC Fibers, 1994. 

4. US Patent 7687016: Methods for Producing Silicon Carbide Architectural Preforms. 

5. J. DiCarlo: Property Goals and Test Methods for High Temperature Ceramic Fiber Reinforcement. 

Ceramics International 23 (1997) 283. 

6. G. Morscher and J. DiCarlo: A Simple Test for Thermomechanical Evaluation of Ceramic Fibers. 

J. Am. Ceram. Soc. 75 [1] (1992) 136. 

7. P. Le Coustumer et al.: Understanding Nicalon Fiber. J. European Cer. Soc. 11 (1993) 95. 

8. J. Biernacki, et al. Scaling Technology for Production of Continuous Ceramic Fiber. Ceramic 

Engineering and Science Proceedings, vol. 18[3], 1997, pp. 73–85.