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Advanced Seal Technology Role in Meeting Next Generation Turbine Engine GoalsCycle studies have shown the benefits of increasing engine pressure ratios and cycle temperatures to decrease engine weight and improve performance in next generation turbine engines. Advanced seals have been identified as critical in meeting engine goals for specific fuel consumption, thrust-to-weight, emissions, durability and operating costs. NASA and the industry are identifying and developing engine and sealing technologies that will result in dramatic improvements and address the goals for engines entering service in the 2005-2007 time frame. This paper provides an overview of advanced seal technology requirements and highlights the results of a preliminary design effort to implement advanced seals into a regional aircraft turbine engine. This study examines in great detail the benefits of applying advanced seals in the high pressure turbine region of the engine. Low leakage film-riding seals can cut in half the estimated 4% cycle air currently used to purge the high pressure turbine cavities. These savings can be applied in one of several ways. Holding rotor inlet temperature (RIT) constant the engine specific fuel consumption can be reduced 0.9%, or thrust could be increased 2.5%, or mission fuel burn could be reduced 1.3%. Alternatively, RIT could be lowered 20 'F resulting in a 50% increase in turbine blade life reducing overall regional aircraft maintenance and fuel bum direct operating costs by nearly 1%. Thermal, structural, secondary-air systems, safety (seal failure and effect), and emissions analyses have shown the proposed design is feasible.
Document ID
Document Type
Conference Paper
Steinetz, Bruce M.
(NASA Lewis Research Center Cleveland, OH United States)
Hendricks, Robert C.
(NASA Lewis Research Center Cleveland, OH United States)
Munson, John
(Allison Engine Co. Indianapolis, IN United States)
Date Acquired
August 19, 2013
Publication Date
February 1, 1999
Publication Information
Publication: Design Principles and Methods for Aircraft Gas Turbine Engines
Subject Category
Aircraft Propulsion And Power
Distribution Limits
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