Technical Topic 3: Advanced Materials; SUBTOPIC 3B: ADVANCED MATERIALS FOR GAS TURBINE COATINGS

The summary for the Technical Topic 3: Advanced Materials; SUBTOPIC 3B: ADVANCED MATERIALS FOR GAS TURBINE COATINGS grant is detailed below. This summary states who is eligible for the grant, how much grant money will be awarded, current and past deadlines, Catalog of Federal Domestic Assistance (CFDA) numbers, and a sampling of similar government grants. Verify the accuracy of the data FederalGrants.com provides by visiting the webpage noted in the Link to Full Announcement section or by contacting the appropriate person listed as the Grant Announcement Contact. If any section is incomplete, please visit the website for the National Energy Technology Laboratory, which is the U.S. government agency offering this grant.

Technical Topic 3: Advanced Materials; SUBTOPIC 3B: ADVANCED MATERIALS FOR GAS TURBINE COATINGS: NOTE: This descriptive area provides an overview of this Funding Opportunity. YOU MUST READ THE FUNDING OPPORTUNITY MASTER ANNOUNCEMENT FOR DETAILS ON ADDITIONAL INFORMATION, EVALUATION CRITERIA AND HOW TO PREPARE AN APPLICATION UNDER A SPECIFIC AREA OF INTEREST. Please scroll to the bottom of this page under the heading Full Announcement and Other Files and click on the link to access the Funding Opportunity Master Announcement. YOU MUST SUBMIT YOUR APPLICATION VIA GRANTS.GOV TO BE CONSIDERED FOR AN AWARD. New materials are required to significantly improve performance and reduce the costs of existing and/or advanced coal-based power systems. New materials are also needed to enable the development of new systems and capabilities for coal combustion, coal gasification, gas separations, hydrogen storage, high-temperature fuel cells, and advanced turbine systems. These materials are expected to perform satisfactorily under hostile conditions such as high temperatures, elevated pressures, pressure oscillations, corrosive environments (oxidizing or reducing conditions, gaseous alkali, chloride or sulfur-containing species), surface coating or fouling, and high particulate loading. Subtopic 3B: Advanced Materials for Gas Turbine Coatings Gas or combustion turbines work at high temperature (over 1300o C) and need protective coatings for the components such as engine blades, vanes, and combustors that experience such high temperatures or come in contact with deleterious substances in the gas stream. The coatings, especialllly those based on ceramics, are broadly categorized as thermal barrier coatings (TBCs) and environmental barrier coatings (EBCs), depending on their primary function. Priorities in the program include the selection and verification testing of turbine hot path component materials and protective coatings when using coal-derived synthesis gas or hydrogen as fuel. Specifically, the thermal barrier functions of EBC apos;s become vital for reducing the engine-component thermal loads and chemical reaction rates, thus maintaining the required mechanical properties and durability of these components. The improvement on the development of TBCs and EBCs will directly impact the successful development of advanced turbines. Differences in synthesis gas composition relative to natural gas due to different gasifier type may also be researched with respect to the interaction of trace contaminants with advanced turbine blade materials and coatings. Synthesis gas contains traces of heavy metals not found in natural gas. The interactions of these trace constituents with the materials and coatings currently being used needs to be investigated. In addition, the presence of particulates may cause erosion or deposition, and gaseous species (e.g. SOx, alkali compounds, HCl) may cause deposition and/or enhance corrosion. Synergistic effects between these degradation processes are also likely under gas turbine operating conditions. All these degradation modes rather than creep and fatigue processes may be limiting the operating life of turbine hot-gas components such as combustion chamber, vanes and blades when using coal-derived synthesis gas as fuel. Thus, hot corrosion and erosion-corrosion models to predict the lives of candidate materials in realistic environments for a gas turbine operating on coal-derived gases are necessary to assess potential lives of such components, and establish changes to these environments which would significantly extend these lives. In the past, the designs for the coatings, especially TBCs for single crystal (SX) turbine blades, were developed through a phenomenological approach. However, today, emphasis is on prime-reliant design (i.e., providing the designer with safe performance criteria) based on sound mechanistic knowledge of gas-solid interactions at high temperatures, and of the way in which these interactions influence the processes involved in degradation during service. Grant applications are sought for high-temperature protective coatings for gas turbines using coal-derived synthesis gas along with a coherent strategy for their development. The aim is to identify the physically attainable limits and to push the operating envelope to that point through prime reliant design. Proposed approaches for the coatings should demonstrate their low thermal conductivity, adhesion, and survivability under operating conditions. Areas of interest include coatings for turbines based on both SX alloys and ceramics. For metallic substrates, separate coating layers may be required for the environmental and thermal barrier functions, whereas for ceramics, it may be possible to fulfill both roles in a single coating layer. Also of interest are manufacturing/coating processes that are airfoil-specific - e.g., coatings for vanes may be different than those for blades (different property/thickness requirements lead to different coating processes, etc.)