Military Jet Engine Acquisition Technology Basics and Cost-Estimating Methodology

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Military Jet Engine Acquisition Technology Basics and Cost-Estimating Methodology ( military-jet-engine-acquisition-technology-basics-and-cost-e )

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142 Military Jet Engine Acquisition pressure spools rotate in opposite directions. (A spool is essentially a compressor and the turbine that drives it, along with the shaft that connects the two rotating components.) All compressor and fan stages are integrally bladed. The fan’s first-stage blades are also hol- low to save weight and enable the engine to respond more rapidly to throttle changes. The F119’s floatwall combustor design should re- duce the problems that are typically associated with thermal stresses in combustor liners (Jane’s Information Group, 1999c). Engine maintenance improvements have been designed into the F119 based on lessons learned from previous engines. For example, almost none of the line replaceable units that are external to the en- gine are stacked on top of one another, fasteners are standardized, and key portions of the external plumbing are flexible hosing. The engine’s main case is split at the fan and at the compressor to permit rapid access to those components. Overall, the engine has 40 percent fewer parts than the F100 (“P&W to Test ...,” 1994). P&W has pre- dicted that engine deployments will require 75 percent less airlift and will require 220 pieces of relatively compact ground support equip- ment, compared with the 400 pieces required by the F100-PW-229. F119 maintenance personnel will use electronic tech manuals, re- placing approximately 85,000 pieces of paper that would have been required with traditional manuals. In addition, electronic updating of these manuals will save extensive flightline maintenance manpower, compared with traditional methods (Kandebo, 1995b). Using the F100-PW-220 as a baseline, P&W expects shop visit rates to be re- duced 74 percent, unscheduled engine removal rates to be reduced 33 percent, and maintenance man hours per flight hour to be re- duced 63 percent (“F119 Configuration ...,” 1991). F135 The P&W F119 was also chosen as the engine to power the JSF demonstrators in the concept development phase. However, the F135, a derivative of the F119-PW-100, is being developed to meet the JSF requirements. Rear Admiral Craig Steidle, former U.S. Navy JSF program director, stated that the propulsion system is the great- est technical challenge for the JSF (Warwick, 1997). For all the JSF variants, maximum thrust will increase from 35,000 pounds to approximately 40,000 pounds. The primary technology

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