Integration Issues of an Ultra-Compact Combustor to a Jet Turbine Engine

Conrad, Matthew M.; Wilson, Jacob D.; Polanka, Marc D.

doi:10.2514/6.2013-3711

Cited by 8 publications

(2 citation statements)

References 6 publications

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“…Rayleigh losses, or pressure loss due to heat addition, are an obstacle for UCC inte gration since the high Mach number in the core tends to increase these losses [8]. More details of the facility design are provided in Conrad et al [9],…”

Section: Fig 4 Afit Full Annulus Ucc Test Rigmentioning

confidence: 98%

Flame Structure Effects at High G-Loading

Wilson

Damele

Polanka

2014

Journal of Engineering for Gas Turbines and Power

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Previous research has been conducted showing significant benefits on combustion effi ciency and stability by creating high gravity-loaded combustion environments. Ultracom pact 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 environ ment 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 differ ent 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 com bustion 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 o f 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.

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Section: Fig 4 Afit Full Annulus Ucc Test Rigmentioning

confidence: 98%

Flame Structure Effects at High G-Loading

Wilson

Damele

Polanka

2014

Journal of Engineering for Gas Turbines and Power

Self Cite

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“…Anisko et al optimized the design of an HGC cavity by designing the blade shape such that the vortex is forced to remain in the annular cavity to further reduce the HGC volume and maximize the use of the annular cavity. Conrad et al designed an HGC with a variable diffuser to separate the pressurizer outlet flow into annular cavity and core flows, which was used to solve the problem of connecting the annular flow to the axial flow. Bohan and Polanka and Blunck et al , further reduced the length and weight of the engine by eliminating the pressurizer outlet guide vanes and combining the UCC with neighboring components.…”

Section: Introductionmentioning

confidence: 99%

Gear-Shaped High-g Combustion Chamber for Micro Turbojet Engine Applications

Huang,

Chen,

long

et al. 2024

ACS Omega

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Enhancing combustion efficiency and optimizing the thrust-toweight ratio are critical technical challenges encountered in the development, application, and growth of micro turbojet engines. The high-centrifugal (high-g) combustion chamber, as an innovative combustion chamber system, has the capability to replace the primary combustion chamber of the traditional turbojet engine, reducing the length of the combustion chamber while maintaining engine performance. Previous studies on the structure of the high-g combustor (HGC) have shown problems such as uneven temperature distribution of the turbojet rotor. To improve the feasibility of HGC integration into micro turbojet engines, this study conducts relevant experiments on a 120 N thrust engine. Subsequently, the results of these experiments were used to analyze the structural design of HGC through a simulation approach. Including six main configurations, the first four structural designs focused on establishing a suitable highly centrifugal environment to stabilize and improve the combustion performance, which was successfully achieved by designing the outer ring gearshaped inlet with four different angles. Subsequent structural designs were based around improving the uniformity of the temperature distribution at the combustion chamber outlet. The final design of the HGC combustion efficiency is not much different from the original combustion chamber, and it can shorten the axial length of the combustion chamber by nearly 30%. The design of the air inlet holes and the baffle plate effectively improves the temperature uniformity at the outlet of the combustion chamber. Moreover, without changing the combustion chamber material, the corresponding engine weight can be reduced by about 10.7%, and the engine thrust-to-weight ratio can be improved by up to 12% with the same thrust, which provides design ideas for further lightweight applications.

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Numerical investigation on the effect of g-load on high-g ultra-compact combustor

Yan

Fan

et al. 2022

Aerospace Science and Technology

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Integration Issues of an Ultra-Compact Combustor to a Jet Turbine Engine

Cited by 8 publications

References 6 publications

Flame Structure Effects at High G-Loading

Flame Structure Effects at High G-Loading

Gear-Shaped High-g Combustion Chamber for Micro Turbojet Engine Applications

Numerical investigation on the effect of g-load on high-g ultra-compact combustor

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