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Multi-Point Combustion System: Final ReportA low-NOx emission combustor concept has been developed for NASA's Environmentally Responsible Aircraft (ERA) program to meet N+2 emissions goals for a 70,000 lb thrust engine application. These goals include 75 percent reduction of LTO NOx from CAEP6 standards without increasing CO, UHC, or smoke from that of current state of the art. An additional key factor in this work is to improve lean combustion stability over that of previous work performed on similar technology in the early 2000s. The purpose of this paper is to present the final report for the NASA contract. This work included the design, analysis, and test of a multi-point combustion system. All design work was based on the results of Computational Fluid Dynamics modeling with the end results tested on a medium pressure combustion rig at the UC and a medium pressure combustion rig at GRC. The theories behind the designs, results of analysis, and experimental test data will be discussed in this report. The combustion system consists of five radially staged rows of injectors, where ten small scale injectors are used in place of a single traditional nozzle. Major accomplishments of the current work include the design of a Multipoint Lean Direct Injection (MLDI) array and associated air blast and pilot fuel injectors, which is expected to meet or exceed the goal of a 75 percent reduction in LTO NOx from CAEP6 standards. This design incorporates a reduced number of injectors over previous multipoint designs, simplified and lightweight components, and a very compact combustor section. Additional outcomes of the program are validation that the design of these combustion systems can be aided by the use of Computational Fluid Dynamics to predict and reduce emissions. Furthermore, the staging of fuel through the individually controlled radially staged injector rows successfully demonstrated improved low power operability as well as improvements in emissions over previous multipoint designs. Additional comparison between Jet- A fuel and a hydrotreated biofuel is made to determine viability of the technology for use with alternative fuels. Finally, the operability of the array and associated nozzles proved to be very stable without requiring additional active or passive control systems. A number of publications have been publish
Document ID
20140006387
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Goeke, Jerry (UTC Aerospace Systems West Des Moines, IA, United States)
Pack, Spencer (UTC Aerospace Systems West Des Moines, IA, United States)
Zink, Gregory (UTC Aerospace Systems West Des Moines, IA, United States)
Ryon, Jason (UTC Aerospace Systems West Des Moines, IA, United States)
Date Acquired
May 28, 2014
Publication Date
April 1, 2014
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/CR-2014-218112
E-18851
Funding Number(s)
CONTRACT_GRANT: NNC11CA15C
WBS: WBS 699959.02.26.03.04.05.09
Distribution Limits
Public
Copyright
Public Use Permitted.

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