Analysis of an Additively Manufactured Cooled Ultra Compact Combustor Vane

DeMarco, Kevin J.; Bohan, Brian T.; Polanka, Marc D.; Rutledge, James L.; Akbari, Pezhman

doi:10.1115/1.4043548

Cited by 4 publications

(3 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Cottle et al 25 added a set of injection plates and baffles to an HGC with a diffuser to control the directions and ratios of the core and secondary streams. Subsequently, Bohan et al 26,27 designed a cooling scheme by designing holes to form a cooling film and hence mitigate the localized overheating problem of the HGC. Zhang et al 6 designed an asymmetric combustion chamber, and the experimental results showed that the combustion efficiency was greater than 94%.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

Huang,

Chen,

long

et al. 2024

ACS Omega

View full text Add to dashboard Cite

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.

show abstract

Section: Introductionmentioning

confidence: 99%

“…Subsequently, Bohan et al , designed a cooling scheme by designing holes to form a cooling film and hence mitigate the localized overheating problem of the HGC. Zhang et al designed an asymmetric combustion chamber, and the experimental results showed that the combustion efficiency was greater than 94%.…”

Section: Introductionmentioning

confidence: 99%

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

Huang,

Chen,

long

et al. 2024

ACS Omega

View full text Add to dashboard Cite

show abstract

“…As well known, gas turbines are numerously used to convert energy of combustio gases into mechanical work. [1][2][3][4][5][6] One main goal in gas turbine engine development is to increase its thermodynamics efficiency, of which the turbine inlet temperature plays a very important role. Evidently, this temperature should not exceed the allowable design temperature of metal parts.…”

Section: Introductionmentioning

confidence: 99%

Internal cooling sensitivity analysis to improve the thermal performance of gas turbine blade using a developed robust conjugate heat transfer method

Darbandi

Jalali

2022

International Journal of Engine Research

View full text Add to dashboard Cite

The heat transfer simulations of turbine blades with internal cooling are faced with so many uncertainties, of which some originate from the secondary air system, including the inlet hot gas temperature and pressure and the cooling side boundary conditions, and the blade material. The main objective of this work is to carry out a suitable sensitivity analysis on a specific novel turbine vane to improve the thermal performance of its internal cooling system and to quantify how the uncertainties on the designed/calculated values can desirably/undesirably affect the maximum blade surface temperature, which can consequently affect the gas turbine engine efficiency. Furthermore, the sensitivity analysis is carried out to find the effects of uncertainties of a number of key parameters on the resulting blade temperature distribution. To arrive at trustworthy conclusions, the conjugate heat transfer (CHT) method is used to analyze the heat and fluid flow behavior. This work suitably develops a CHT-based method/solver to perform the proposed study. This method/solver uses a segregated iterative procedure, in which the outer hot gas region is simulated using the computational fluid dynamics (CFD) solver, the flow passing through the connected internal cooling passages is calculated using a 1D correlated-based solver, and the vane conduction is predicted using a 3D finite-element solver, which are fully coupled. The results show that the cooling channel wall temperature has a direct impact on the convective coefficient magnitude; especially in lower temperature regions. As a novel contribution, this work takes into account the cooling wall temperature influence on the 1D code calculations. To implement this, an artificial neural network is suitably trained to predict better convective coefficient. The results of this developed CFD-CHT code are validated against experimental data available for a benchmark vane. Eventually, the sensitivity analysis is carried on the present specific novel turbine vane.

show abstract

A New Design of a Pinwheel-Shaped High-G Combustor

Liu

Wang

Tang

2021

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

High-g combustor (HGC) is a significant branch of the ultracompact combustor, an innovative gas turbine combustor with the ability to shorten the combustor length and improve engine efficiency. To improve the feasibility of the HGC concept, a new HGC was designed to substitute the conventional combustor of a KJ66 small turbine engine. The KJ66 was modified to fit an instrumentation system and test bench to conduct relative experiments. Based on the experiment results, design iterations were conducted relying on simulation methods. The design iteration was comprised of six primary configurations, of which the first four configurations focused on establishing an appropriate high-centrifugal environment to accelerate primary combustion, while the last two modifications focused on improving overall combustion performance. In configuration 4, a pinwheel-shaped swirl inlet was designed to successfully create the high-g environment and balance the flow distribution while bringing insignificant total pressure loss. One modification of configuration 4 was a grid inlet design that divided the inlet channel into several subchannels to constrain the inlet flow and establish an ideal high-g environment. The other modification was a divergent mainstream channel to encourage the dilution process and improve the exit temperature profile. The final design could save at least 1/3 of combustor length while maintaining the same level of performance as the original combustor. Further, the engine was predicted to save at least 12% of the total engine weight and improve at least 14% of the engine thrust-to-weight ratio.

show abstract

Analysis of an Additively Manufactured Cooled Ultra Compact Combustor Vane

Cited by 4 publications

References 17 publications

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

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

Internal cooling sensitivity analysis to improve the thermal performance of gas turbine blade using a developed robust conjugate heat transfer method

A New Design of a Pinwheel-Shaped High-G Combustor

Contact Info

Product

Resources

About