Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

Schnoes, Markus; Voß, C.; Nicke, Eberhard

doi:10.22261/jgpps.w5n91i

Cited by 24 publications

(18 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Using the 2D TF code ACDC [6] developed at the DLR, a compressor has been modelled and simulated. Through a 'Design of Experiments' (DoE), several levels of outlet flow reduction, achieved by different distributions of BO extraction, have been simulated.…”

Section: Blow-off Studiesmentioning

confidence: 99%

Compressor Retrofittable Solutions in Heavy-Duty Gas Turbines for Minimum Environmental Load Reduction

et al. 2019

View full text Add to dashboard Cite

International policies aiming at keeping global warming within safety limits will strongly impact gas-fired power plants. Flexibility is going to be the key-word, hence this paper focuses on possible strategies to increase turndown capability (i.e. lowering Minimum Environmental Load (MEL)) of open and combined cycle power plants (CCPP) through retrofittable compressor service packages. In particular, the following three options have been analyzed: extra-closure of Variable Inlet Guide Vanes (IGVs), Blow-Off (BO) lines opening and inlet bleed heating. All these solutions aim at reducing the compressor outlet mass-flow rate while keeping a safe stability margin. The effect of lowering the minimum load capability by opening the BO lines has been numerically investigated through full compressor 2D throughflow analyses. Moreover, the impact on compressor performance and stability of the extra-closure of IGVs has been analyzed with the support of 3D steady-state CFD modelling. Finally, the overall performance of the power-plant has been included and discussed in order to provide plant managers with a solid starting point for a techno-economic analysis.

show abstract

Section: Blow-off Studiesmentioning

confidence: 99%

Compressor Retrofittable Solutions in Heavy-Duty Gas Turbines for Minimum Environmental Load Reduction

et al. 2019

View full text Add to dashboard Cite

show abstract

“…The conceptual design of the aft-propulsor was carried out using a streamline-curvature method in a through-flow manner using the DLR's Advanced Compressor Design Code (ACDC) [20,21]. This study focused on this particular component, due to the more unknown, and to some extent, unconventional design space (as compared with the main engine component).…”

Section: Propulsor Conceptual Designmentioning

confidence: 99%

“…The second mode enables the assessment at off-design conditions and the calculation of respective performance characteristics over the entire speed range. Both modes assess the fan design by taking advantage of a large database of pre-optimized profiles (see References [20,21] for more details), together with standard correlations taking into account endwall and tip leakage effects. One of the advantages of the existing database is that it consists of performance parameters, such as profile losses and deviation being directly linked to geometric parameters.…”

Section: Propulsor Conceptual Designmentioning

confidence: 99%

“…Computational grid and station definition as input parameters to the streamline-curvature method ACDC (Advanced Compressor Design Code [20,21]) used for the aft-propulsor conceptual design.…”

Section: Figurementioning

confidence: 99%

“…Although some effort was put into realizing this direct coupling procedure, it only seems to have advantages when creating maps being more computationally expensive (e.g., by CFD) than being achieved with a through-flow based approach (which needs less than a minute to produce the entire map). [20,21]) used for the aft-propulsor conceptual design.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Assessment of a Turbo-Electric Aircraft Configuration with Aft-Propulsion Using Boundary Layer Ingestion

et al. 2019

Self Cite

View full text Add to dashboard Cite

In this paper, a turbo-electric propulsion system was analyzed, and its performance was assessed. The aircraft considered here was a single-aisle, medium-range configuration targeting a capacity of 150 Pax. The propulsion concept comprised two boosted geared turbofan engines mounted under-wing. Those main engines were supported by an electrically driven aft-propulsor contributing to the thrust generation and by taking advantage of ingesting the boundary layer of the fuselage for potentially higher levels of propulsive efficiency and allowing for the improved operation of the main engines. The performance assessment as carried out in the context of this paper involved different levels: Firstly, based on the reference aircraft and the detailed description of its major components, the engine performance model for both main engines, as well as for the electrically driven aft-propulsor was set up. The methodology, as introduced, has already been applied in the context of hybrid-electric propulsion and allowed for the aforementioned aircraft sizing, as well as the subsequent gas turbine multi-point synthesis (simulation). A geared turbofan architecture with 2035 technology assumptions was considered for the main engine configuration. The present trade study focused on the design and performance analysis of the aft-propulsor and how it affected the performance of the main engines, due to the electric power generation. In order to allow for a more accurate description of the performance of this particular module, the enhanced streamline curvature method with an underlying and pre-optimized profile database was used to design a propulsor tailored to meet the requirements of the aft propulsor as derived from the cycle synthesis and overall aircraft specification; existing design expertise for novel and highly integrated propulsors could be taken advantage of herein. The resulting performance characteristics from the streamline curvature method were then fed back to the engine performance model in a closely coupled approach in order to have a more accurate description of the module behavior. This direct coupling allowed for enhanced sensitivity studies, monitoring different top-level parameters, such as the thrust/power split between the main engines and the aft propulsor. As a result, different propulsor specifications and fan designs with optimal performance characteristics were achieved, which in return affected the performance of all subsystems considered.

show abstract

Sensitivity Study of Stagger Angle on the Aerodynamic Performance of Transonic Axial Flow Compressors

Dalbanjan

Sarangi

2022

Proceedings of the National Aerospace Propulsion Conference

View full text Add to dashboard Cite

Design optimization of a multi-stage axial compressor using throughflow and a database of optimal airfoils

Cited by 24 publications

References 16 publications

Compressor Retrofittable Solutions in Heavy-Duty Gas Turbines for Minimum Environmental Load Reduction

Compressor Retrofittable Solutions in Heavy-Duty Gas Turbines for Minimum Environmental Load Reduction

Assessment of a Turbo-Electric Aircraft Configuration with Aft-Propulsion Using Boundary Layer Ingestion

Sensitivity Study of Stagger Angle on the Aerodynamic Performance of Transonic Axial Flow Compressors

Contact Info

Product

Resources

About