Stuart C. Greenfield, Paul V. Heberling, and George E. MoertleGeneral Electric Aircraft Engines, Cincinnati, Ohio

HSCT Sector Combustor HardwareModifications for Improved Combustor Design

NASA/CR—2005-213322

January 2005

https://ntrs.nasa.gov/search.jsp?R=20050061010 2020-03-02T21:32:49+00:00Z

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Stuart C. Greenfield, Paul V. Heberling, and George E. MoertleGeneral Electric Aircraft Engines, Cincinnati, Ohio

HSCT Sector Combustor HardwareModifications for Improved Combustor Design

NASA/CR—2005-213322

January 2005

National Aeronautics andSpace Administration

Glenn Research Center

Prepared under Contract NAS3–26617

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Document History

This research was originally published internally as HSR030 in January 1996.

Note that at the time of writing, the NASA Lewis Research Centerwas undergoing a name change to the

NASA John H. Glenn Research Center at Lewis Field.Both names may appear in this report.

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75

HSCT Sector Combustor Hardware Modifications for ImprovedCombustor Design

Stuart C. Greenfield, Paul V. Heberling, and George E. Moertle

High speed civil transport; Lean premixed prevaporized (LPP) combustor; Integrated mixerflameholder (IMFH) tubes; Cyclone swirler pilot; NOx emissions

Unclassified -UnlimitedSubject Categories: 01, 05, and 07 Distribution: Nonstandard

General Electric Aircraft EnginesAdvanced Engineering Programs DepartmentOne Neumann WayCincinnati, Ohio 45215–6301

This research was originally published internally as HSR030 in January 1996. Responsible person, Diane Chapman,Ultra-Efficient Engine Technology Program Office, NASA Glenn Research Center, organization code PA,216–433–2309.

An alternative to the stepped-dome design for the lean premixed prevaporized (LPP) combustor has been developed.The new design uses the same premixer types as the stepped-dome design: integrated mixer flameholder (IMFH) tubesand a cyclone swirler pilot. The IMFH fuel system has been taken to a new level of development. Although the IMFHfuel system design developed in this Task is not intended to be engine-like hardware, it does have certain characteristicsof engine hardware, including separate fuel circuits for each of the fuel stages. The four main stage fuel circuits areintegrated into a single system which can be withdrawn from the combustor as a unit. Additionally, two new types ofliner cooling have been designed. The resulting lean blowout data was found to correlate well with the Lefebvreparameter. As expected, CO and unburned hydrocarbons emissions were shown to have an approximately linearrelationship, even though some scatter was present in the data, and the CO versus flame temperature data showed thetypical cupped shape. Finally, the NOx emissions data was shown to agree well with a previously developed correlationbased on emissions data from Configuration 3 tests performed at GEAE. The design variations of the cyclone swirlerpilot that were investigated in this study did not significantly change the NOx emissions from the baseline design(GEAE Configuration 3) at supersonic cruise conditions.