| Last Name | Name | Awards | Contact | |
|---|---|---|---|---|
| Nagpal | Dr. Vinod K. Nagpal | 15 | Message | |
| Gyekenyesi | Dr. John Z. Gyekenyesi | 1 | ||
| Prakash | Amit Prakash | 1 | Message | |
| Strack | William Strack | 1 | Message | |
| Boyle | Robert Boyle | 4 | Message | |
| Gayda | John Gayda Jr. | 2 | Message | |
| Miller | Ian T Miller | 1 | Message |
Phase 1 SBIR
The proposal is to identify cycle improvements and verify structural feasibility of shrouding a low aspect ratio High Pressure Turbine(HPT) rotor designed to use ceramic blades. When the clearance-to-span ratio between the rotating blades and the stationary casing is the same as the clearance-to-span ratio between the rotating shroud and the sta...
Phase 1 SBIR
The proposal is for the design of a fan duct heat exchanger in order to improve aircraft fuel burn. The fan duct heat exchanger decreases the temperature of the 15% to 20% of compressor discharge air used to cool the High Pressure Turbine(HPT). Reducing the HPT cooling air temperature reduces the amount of cooling air needed for HPT cooling, and...
Phase 1 SBIR
The proposed work will develop a reliability analysis tool consistent with conceptual-level design for ceramic matrix composite (CMC) turbine blades and vanes. The analysis software will comprise a suite of physics-based discipline specific analysis code modules and NASA's Fast Probability Integrator (FPI). The objective of this analysis tool is...
Phase 1 SBIR
ABSTRACT:This program implements a Bayesian framework for uncertainty quantification of material parameters needed for life prediction of polymer matrix composite (PMC) bolted joints. Accurate estimations of fatigue strength parameters and their distributions are needed for durability assessment of composite airframes with bolted joints. The pro...
Phase 1 SBIR
This proposal presents a hybrid metal-CMC turbine blade. A SiC/SiC CMC airfoil section will be bonded to a single crystal superalloy root section in order to mitigate risks associated with an all-CMC blade inserted in a superalloy disk. This allows current blade attachment technology (SX blade with a dovetail attachment to a slotted Ni disk) ...
Phase 1 SBIR
A finite element based model will be developed and validated to capture the evolution of residual stresses and cold work at machined features of compressor and turbine powder metallurgy superalloy disks. The focus will be to quantify, model and validate residual stress and cold work evolution at stress concentration features during simulated ser...
Phase 2 SBIR
The work proposed herein is to demonstrate that the higher temperature capabilities of Ceramic Matrix Composites (CMC) can be fully utilized to reduce emissions and improve fuel consumption in gas turbine engines. The work involves closely coupling aerothermal and structural analyses for the first stage vane of a high pressure turbine (HPT). T...
Phase 1 STTR
Institution: University of Arizona
The Phase I deliverable will be a physic-based model which represents a CMC gas turbine component concomitantly at the material level and the structural level. This model will be probabilistically analyzed to account for the uncertainties in material properties and the uncertainties in the size and impact velocities of possible foreign objects (...
Phase 1 SBIR
N&R Engineering will investigate the feasibility of cooled ceramics, such as ceramic matrix composite (CMC) turbine blade concepts that can decrease specific fuel consumption while reducing NOX emissions. The conflict between efficiency and emissions will require a careful balancing of material selection, turbine inlet temperature, and cooling ...
Phase 1 SBIR
Composite materials are being used in greater quantities for military combat vehicles and other hardware in an effort to improve the overall performance by making them lighter, stiffer, and have greater damage tolerance. The operating environment for military may present unique hazards such as projectiles from small arms and shrapnel. These haza...
