0
Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Flame Structure Effects at High G-Loading

[+] Author and Article Information
Jacob D. Wilson, Christopher J. Damele

Air Force Institute of Technology,
Wright-Patterson AFB, OH 45433

Marc D. Polanka

Air Force Institute of Technology,
Wright-Patterson AFB, OH 45433
e-mail: Marc.Polanka@afit.edu

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 5, 2014; final manuscript received March 3, 2014; published online May 2, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(10), 101502 (May 02, 2014) (8 pages) Paper No: GTP-14-1068; doi: 10.1115/1.4027128 History: Received February 05, 2014; Revised March 03, 2014

Previous research has been conducted showing significant benefits on combustion efficiency and stability by creating high gravity-loaded combustion environments. Ultracompact combustor systems decrease the size and weight of the overall engine by integrating the compressor, combustor, and turbine stages. In this system, the core flow is split and a portion is routed into a circumferential direction to be burned at a high equivalence ratio. Fuel and air are brought into the cavity and combusted in a high g-loaded environment driven by air injection. Computational research showed that the hole diameter of the air injection jets are directly related to g-loading within the cavity. An experimental rig was built where the air injection rings could be changed to contain one of three different jet hole diameters to verify this result. The smallest air injection diameter achieved the highest g-loading in the cavity, which is consistent with the computational fluid dynamics (CFD) results. However, the flame stability within the cavity was affected by the air injection jet becoming too large or too small for a particular equivalence ratio. Video taken at 8000 Hz was used to capture the flame structure, revealing that the flame was not stable even before lean blow out conditions were achieved. Additionally, the direction that the air jets swirled in the cavity was found to have an impact on the combustion dynamics. When flow swirled counterclockwise and impacted the suction side of the turbine vane, the cavity had a more uniform fully developed flow field, as opposed to the pressure side impact. Finally, liquid fuel testing was done to test the atomization and mixing of JP-8 in a g-loaded environment. The results showed that increasing the cavity g-load increased the residence time the fuel stayed in the cavity.

FIGURES IN THIS ARTICLE
<>
Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Representative UCC setup (above) compared to a typical combustor (below) [3]

Grahic Jump Location
Fig. 2

Stability limits of the AFRL UCC test rig [6]

Grahic Jump Location
Fig. 5

Migration flow path for CW (left) and CCW (right)

Grahic Jump Location
Fig. 4

AFIT full annulus UCC test rig

Grahic Jump Location
Fig. 3

Relationship between the cavity air jet diameter, velocity, and tangential velocity [3]

Grahic Jump Location
Fig. 7

Cavity driver rings with different air injection diameters

Grahic Jump Location
Fig. 6

Camera and mirror positioning (left) and mirror visualization (right)

Grahic Jump Location
Fig. 10

Lean blow out for a constant core flow of 3.24 kg/min

Grahic Jump Location
Fig. 11

Average flame intensity (50 frames each) with decreasing equivalence ratio

Grahic Jump Location
Fig. 12

G-loading data for 3.24 kg/min core and ϕ = 1.76

Grahic Jump Location
Fig. 8

CW (left) and CCW (right) instantaneous flame intensities

Grahic Jump Location
Fig. 9

CW (left) and CCW (right) averaged flame intensities (50 frames)

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In