scholarly journals Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl

2021 ◽  
Author(s):  
Xing Yang ◽  
Zihan Hao ◽  
Zhenping Feng
Keyword(s):  
High Pressure ◽  
Particle Deposition ◽  
High Pressure Turbine ◽  
Deposition Patterns ◽  
Turbine Vanes ◽  
Inlet Swirl

Effect of Combustor Swirl on Transonic High Pressure Turbine Efficiency

2013 ◽  
Vol 136 (1) ◽  
Author(s):  
Paul F. Beard ◽  
Andy D. Smith ◽  
Thomas Povey
Keyword(s):  
High Pressure ◽  
Computational Study ◽  
Pressure Ratio ◽  
High Pressure Turbine ◽  
Turbine Efficiency ◽  
Baseline Case ◽  
Inlet Swirl ◽  
Computational Fluid Dynamics Cfd ◽  
External Flows ◽  
The Eu

This paper presents an experimental and computational study of the effect of inlet swirl on the efficiency of a transonic turbine stage. The efficiency penalty is approximately 1%, but it is argued that this could be recovered by correct design. There are attendant changes in capacity, work function, and stage total-to-total pressure ratio, which are discussed in detail. Experiments were performed using the unshrouded MT1 high-pressure turbine installed in the Oxford Turbine Research Facility (OTRF) (formerly at QinetiQ Farnborough): an engine scale, short duration, rotating transonic facility, in which M, Re, Tgas/Twall, and N/T01 are matched to engine conditions. The research was conducted under the EU Turbine Aero-Thermal External Flows (TATEF II) program. Turbine efficiency was experimentally determined to within bias and precision uncertainties of approximately ±1.4% and ±0.2%, respectively, to 95% confidence. The stage mass flow rate was metered upstream of the turbine nozzle, and the turbine power was measured directly using an accurate strain-gauge based torque measurement system. The turbine efficiency was measured experimentally for a condition with uniform inlet flow and a condition with pronounced inlet swirl. Full stage computational fluid dynamics (CFD) was performed using the Rolls-Royce Hydra solver. Steady and unsteady solutions were conducted for both the uniform inlet baseline case and a case with inlet swirl. The simulations are largely in agreement with the experimental results. A discussion of discrepancies is given.

Hybrid RANS/LES Simulation of Combustor/Turbine Interactions

2020 ◽  
Author(s):  
Guoping Xia ◽  
Georgi Kalitzin ◽  
Jin Lee ◽  
Gorazd Medic ◽  
Om Sharma
Keyword(s):  
High Pressure ◽  
Thermal Field ◽  
Numerical Study ◽  
High Fidelity ◽  
Critical Aspect ◽  
High Pressure Turbine ◽  
Cfd Simulations ◽  
Turbine Inlet ◽  
Durability Design ◽  
Turbine Vanes

Abstract Accurate prediction of thermal field in high pressure turbines is a critical aspect of aerodynamic and durability design. This is particularly true when the flow at turbine inlet exhibits large gradients in temperature, both radially and circumferentially. In other words, in the presence of hot streaks from the combustor. In the numerical study presented in this paper, coupled high-fidelity eddy-resolving simulations of a combustor and a turbine are used to study the differences in the temperature profile at the exit of the first vane and the heat flux on the first blade, resulting from different positioning, or clocking, between the combustor fuel nozzles and turbine vanes. The resolved unsteadiness and turbulence from the combustor impacts mixing and secondary flow in the high pressure turbine. Temperature profiles from both actual combustor CFD simulations, as well as and modulated profiles with more pronounced variation, or pattern factor, are used at the turbine inlet. A threshold of the pattern factor that brings the benefit of clocking is identified. Clocking positioning between the combustor and vanes was studied for the most benefit.

scholarly journals Computational Simulation of Deposition in a Cooled High-Pressure Turbine Stage With Hot Streaks

2017 ◽  
Vol 139 (9) ◽  
Author(s):  
Robin Prenter ◽  
Ali Ameri ◽  
Jeffrey P. Bons
Keyword(s):  
High Pressure ◽  
Particle Deposition ◽  
Particle Temperature ◽  
Computational Simulation ◽  
Stokes Number ◽  
Navier Stokes ◽  
Inlet Temperature ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Tracking Model

Ash particle deposition in a high-pressure turbine stage was numerically investigated using steady Reynolds-averaged Navier-Stokes (RANS) and unsteady Reynolds-averaged Navie-Stokes (URANS) methods. An inlet temperature profile consisting of Gaussian nonuniformities (hot streaks) was imposed on the vanes, with vane cooling simulated using a constant vane wall temperature. The steady case utilized a mixing plane at the vane–rotor interface, while a sliding mesh was used for the unsteady case. Corrected speed and mass flow were matched to an experiment involving the same geometry, so that the flow solution could be validated against measurements. Particles ranging from 1 to 65 μm were introduced into the vane domain, and tracked using an Eulerian–Lagrangian tracking model. A novel particle rebound and deposition model was employed to determine particles' stick/bounce behavior upon impact with a surface. Predicted impact and capture distributions for different diameters were compared between the steady and unsteady methods, highlighting effects from the circumferential averaging of the mixing plane. The mixing plane simulation was found to generally under predict impact and capture efficiencies compared with the unsteady calculation, as well as under predict particle temperature upon impact with the blade surface. Quantitative impact and capture efficiency trends with the Stokes number are discussed for both the vane and blade, with companion qualitative distributions for the different Stokes regimes.

Deposition of Volcanic Materials in the Hot Sections of Two Gas Turbine Engines

1993 ◽  
Vol 115 (3) ◽  
pp. 641-651 ◽  
Author(s):  
J. Kim ◽  
M. G. Dunn ◽  
A. J. Baran ◽  
D. P. Wade ◽  
E. L. Tremba
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Volcanic Ash ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
High Pressure Turbine ◽  
Deposition Behavior ◽  
Turbine Engine ◽  
Turbine Vanes ◽  
Volcanic Ash Cloud

This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high-pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, NM. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high-pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combustor. A rather large turbine inlet temperature range can be achieved using these two combustors. The deposition behavior of volcanic materials as well as some of the parameters that govern whether or not these volcanic ash materials melt and are subsequently deposited are discussed.

scholarly journals Monte Carlo Predictions of Aero-Engine Performance Degradation Due to Particle Ingestion

Aerospace ◽  
2021 ◽  
Vol 8 (6) ◽  
pp. 146
Author(s):  
Matthew Ellis ◽  
Nicholas Bojdo ◽  
Antonio Filippone ◽  
Rory Clarkson
Keyword(s):  
High Pressure ◽  
Monte Carlo ◽  
Particle Deposition ◽  
Monte Carlo Model ◽  
Engine Performance ◽  
Performance Data ◽  
High Pressure Turbine ◽  
Particle Cloud ◽  
Validation Data ◽  
Particle Properties

Aero-engines, which encounter clouds of airborne particulate, experience reduced performance due to the deposition of particles on their high-pressure turbine nozzle guide vanes. The rate of this degradation depends on particle properties, engine operating state and the duration of exposure to the particle cloud, variables that are often unknown or poorly constrained, leading to uncertainty in model predictions. A novel method coupling one-dimensional gas turbine performance analysis with generalised predictions of particle deposition is developed and applied through the use of Monte Carlo simulations to better predict high-pressure turbine degradation. This enables a statistical analysis of deterioration from which mean performance losses and confidence intervals can be defined, allowing reductions in engine life and increased operational risk to be quantified. The method is demonstrated by replicating two particle cloud encounter events for the Rolls-Royce RB211-524C engine and is used to predict empirical particle properties by correlating measured engine performance data with Monte Carlo model inputs. Potential improvements in the confidence of these predictions due to more tightly constrained input and validation data are also demonstrated. Finally, the potential combination of the Monte Carlo coupled degradation model with in-service engine performance data and particle properties determined through remote or in situ sensing is outlined and its role in a digital twin to enable a predictive approach to operational capability is discussed.

EBFOG: Deposition, Erosion, and Detachment on High-Pressure Turbine Vanes

2018 ◽  
Vol 140 (6) ◽  
Author(s):  
Nicola Casari ◽  
Michele Pinelli ◽  
Alessio Suman ◽  
Luca di Mare ◽  
Francesco Montomoli
Keyword(s):  
High Pressure ◽  
Gas Turbines ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Flight Crew ◽  
High Pressure Turbine ◽  
Turbine Performance ◽  
Turbine Vanes ◽  
Volcanic Ash Cloud ◽  
Engine Stability

Fouling and erosion are two pressing problems that severely affect gas turbine performance and life. When aircraft fly through a volcanic ash cloud, the two phenomena occur simultaneously in the cold as well as in the hot section of the engine. In the high-pressure turbine (HPT), in particular, particles soften or melt due to the high gas temperatures and stick to the wet surfaces. The throat area, and hence the capacity, of the HPT is modified by these phenomena, affecting the engine stability and possibly forcing engine shutdown. This work presents a model for deposition and erosion in gas turbines and its implementation in a three-dimensional Navier–Stokes solver. Both deposition and erosion are taken into account, together with deposit detachment due to changed flow conditions. The model is based on a statistical description of the behavior of softened particles. The particles can stick to the surface or can bounce away, eroding the material. The sticking prediction relies on the authors' Energy Based FOulinG (EBFOG) model. The impinging particles which do not stick to the surface are responsible for the removal of material. The model is demonstrated on a HPT vane. The airfoil shape evolution over the exposure time as a consequence of the impinging particles has been carefully monitored. The variation of the flow field as a consequence of the geometrical changes is reported as an important piece of on-board information for the flight crew.

STUDI KERUSAKAN HIGH PRESSURE TURBINE VANE PESAWAT ATR72-500 WINGS AIR DI BANDARA SULTAN SYARIF KASIIM II PEKANBARU

2020 ◽  
Vol 7 (1) ◽  
pp. 104-110
Author(s):  
Muhammad Desmico Ekta W ◽  
Abrar Ridwan
Keyword(s):  
High Pressure ◽  
Combustion Chamber ◽  
Gas Flow ◽  
Inlet Temperature ◽  
High Pressure Turbine ◽  
Engine Efficiency ◽  
Turbine Vanes ◽  
Turbine Vane ◽  
Gas Efficiency ◽  
Increasing Temperature

The aircraft can fly as there is a thrust from the engine that causes the aircraft to have speed. The components of the aircraft engines are compressor, combustion chamber, turbine and propeller. High pressure turbine vanes is a component in the Hot section or turbine section that serves to direct the hot gas flow from the combustion chamber to the turbine. The purpose to be achieved in this research is to analyze and find out the cause of high pressure turbine vane damage and know the gas engine efficiency PW127. Cause of damage due to treatment not done according to the schedule until the phenomenon of overtemperature after combustion chamber and the content of impurities in the water laundering results. After the Brayton cycle calculation is obtained the temperature value of the turbine entry 1563oC (1836 K). These results exceed the turbine inlet temperature according to manual maintenance engine. Based on laboratory test, the content of 250 mg/m2 sulfur and 1800 mg/m2 chloride is obtained. This content causes damage by erosion or corrosion of high pressure turbine vane components.  The value of gas efficiency is 42% according to the outside Air tempetarure. The thermal efficiency of gases will increase with increasing temperature conditions.

Analysis of Combustor/Vane Interaction With Decoupled and Loosely Coupled Approaches

2012 ◽  
Author(s):  
Simone Salvadori ◽  
Giovanni Riccio ◽  
Massimiliano Insinna ◽  
Francesco Martelli
Keyword(s):  
High Pressure ◽  
Data Exchange ◽  
Operating Conditions ◽  
Computational Grids ◽  
Test Case ◽  
High Pressure Turbine ◽  
Loosely Coupled ◽  
Section Data ◽  
Turbine Vane ◽  
Inlet Swirl

Numerical techniques are commonly used during both design and analysis processes, mainly considering separated components. Technological progress asks for advanced approaches that allow to analysing the interaction between the components, especially when considering combustor/turbine interaction. Hot spots and inlet swirl profiles generated by the combustor have been demonstrated to affect high-pressure turbine performances and reliability. This work deals with the investigation of the effects of realistic boundary conditions for the high-pressure turbine vane, also proposing an approach for coupled simulation of the combustor/vane interaction. The method consists in a loosely coupled approach for the data exchange on the combustor/vane interface section. Data from the combustor exit section (stagnation conditions, velocity profile and turbulent quantities) are provided to the vane inlet and vice versa (for the static pressure). The proposed method is applied to a test case consisting of a redesigned combustor and the vane of the MT1 test case from QinetiQ. A preliminary analysis was dedicated to define the combustor geometry and the operating conditions. Then, the MT1 working conditions have been rescaled and coupled with the combustor, maintaining the stage geometry and the experimental non-dimensional parameters. Second order accurate steady simulations were performed for both combustor and high-pressure turbine vane. Calculations with a uniform profile and a theoretical nonuniform inlet profile (deriving from the EU funded TATEF2 project) have been considered as representative of commonly used approaches. The results obtained for the stator in terms of isentropic Mach number and Nusselt number along blades surfaces and inner end-wall are compared with each other and with the available experimental data. Due to the large dimension of computational grids a parallel approach was applied. The activity was carried out using the IBM PLX supercomputer in the frame of the FrUIT project supported by CINECA.

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