NASA Glenn Combustion Research for Aeronautical Propulsion

Chang, Clarence T.; Tacina, Kathleen M.; Lee, Chang Sik; Bulzan, Daniel L.; Hicks, Yolanda R.; Liu, N; Lee, J

doi:10.1061/(asce)as.1943-5525.0000289

Cited by 4 publications

(2 citation statements)

References 37 publications

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“…In most of cases, combustion stabilization is not attained over a full range of operating conditions, but limited to only a certain range of conditions, e.g., specific fuel and oxidizer mass flows [6,7], specific inlet fuel and oxidizer temperatures [8], specific chamber outlet boundary conditions [9], and specific fuels [8,[10][11][12]. In practice, fuel and oxidizer mass flows are increased to produce high power output.…”

Section: Introductionmentioning

confidence: 99%

Thermoacoustic Stability Boundaries in the Model Combustion Chamber with a Gas-Centered Swirl Coaxial Injector

Min

Sohn

Yoon

2019

International Journal of Aerospace Engineering

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The stability of a combustion chamber with a gas-centered swirl coaxial injector is investigated over a wide range of operating conditions in the aspect of thermoacoustic instabilities. First, flame shapes induced by the injector are analyzed for various recess lengths from experimental results. The spreading angle and flame size are reduced as the recess length increases. And, as a stability criterion, the damping factor is introduced. The operating conditions are divided into 7 sets with 9 tests, and fuel mass flow is fixed in each set. Stability boundaries are identified in terms of damping factor for the 63 tests by experiments without external perturbations. The stability map for the self-excited instability is obtained and it reveals two unstable regions. One is located at low dynamic head ratio and the other one is at high dynamic head ratio. A stable region is found at moderate dynamic head ratios. Relative stability is evaluated by various flow parameters over a wide range of operating conditions in the combustion chamber with a gas-centered swirl coaxial injector.

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Section: Introductionmentioning

confidence: 99%

Thermoacoustic Stability Boundaries in the Model Combustion Chamber with a Gas-Centered Swirl Coaxial Injector

Min

Sohn

Yoon

2019

International Journal of Aerospace Engineering

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“…NASA has been driving the NOx reduction effort in the aviation industry over the last four decades [1], resulting in approximately 50% reduction every generation of about 15 years ( Figure 1). The initial concerns were health issues such as ground-level NOx and its contribution to photochemical smog.…”

Section: Introductionmentioning

confidence: 99%

NASA Environmentally Responsible Aviation Project Develops Next-Generation Low-Emissions Combustor Technologies (Phase I)

Lee¹

2013

J Aeronaut Aerospace Eng

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NASA's Environmentally Responsible Aviation (ERA) Project is working with industry to develop the fuel flexible combustor technologies for a new generation of low-emissions engine targeted for the 2020 timeframe. These new combustors will reduce Nitrogen Oxide (NOx) emissions to half of current state-of-the-art (SOA) combustors, while simultaneously reducing noise and fuel burn. The purpose of the low NOx fuel-flexible combustor research is to advance the Technology Readiness Level (TRL) and Integration Readiness Level (IRL) of a low NOx, fuel flexible combustor to the point where it can be integrated in the next generation of aircraft. To reduce project risk and optimize research benefit NASA chose to found two Phase 1 contracts. The first Phase 1 contracts went to engine manufactures and were awarded to: General Electric Company, and Pratt & Whitney Company. The second Phase 1 contracts went to fuel injector manufactures Goodrich Corporation, Parker Hannifin Corporation, and Woodward Fuel System Technology. In 2012, two sector combustors were tested at NASA's ASCR. The results indicated 75% NOx emission reduction below the 2004 CAEP/6 regulation level.

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Market Survey and Mission Specification

Sforza¹

2014

Commercial Airplane Design Principles

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NASA Glenn Combustion Research for Aeronautical Propulsion

Cited by 4 publications

References 37 publications

Thermoacoustic Stability Boundaries in the Model Combustion Chamber with a Gas-Centered Swirl Coaxial Injector

Thermoacoustic Stability Boundaries in the Model Combustion Chamber with a Gas-Centered Swirl Coaxial Injector

NASA Environmentally Responsible Aviation Project Develops Next-Generation Low-Emissions Combustor Technologies (Phase I)

Market Survey and Mission Specification

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