Experimental and Numerical Investigation of a Combustor Model

2011 ◽  
Author(s):  
Darioush G. Barhaghi ◽  
Jacek Janczewski ◽  
Thomas Larsson
Keyword(s):  
Mach Number ◽  
Cross Sections ◽  
Load Condition ◽  
Atmospheric Condition ◽  
Flow Distribution ◽  
Scale Model ◽  
Pressure Distributions ◽  
Pressure Recovery Factor ◽  
Measured Pressure ◽  
Different Parts

Fluid flow behaviour is studied both experimentally and numerically in a combustor model which is recently designed at Siemens Turbomachinery AB at Finspong. The model consists of a full size combustor sector that is surrounded by two half size combustor sectors. The half size sectors provide the pressure drop equal to a full scale combustor sector to guarantee the correct air mass flow distribution through the system. Measurements are performed at atmospheric condition and therefore the boundary conditions are scaled based on the Mach number. This means that the Mach number in different parts of the combustor under the test condition is equal to the Mach number of the flow at full load condition. Pitot tubes and pressure taps are employed to measure the dynamic and static pressures at different cross sections of the model. From the measured pressure, the velocity is calculated. The pressure distributions along the diffusers are compared and the pressure recovery factor is calculated for different cases. The computations are performed using RANS (SST k-ω model) and LES (Smagorinsky sub-grid scale model) methods. The computed and measured results show similar trends although there are rather large discrepancies between the results.

Measured Pressure Distributions and Shock Shapes on a Simple Delta Wing

1981 ◽  
Vol 32 (3) ◽  
pp. 188-198 ◽  
Author(s):  
L.C. Squire
Keyword(s):  
Experimental Investigation ◽  
Mach Number ◽  
Delta Wing ◽  
Numerical Calculations ◽  
Test Case ◽  
Pressure Distributions ◽  
Shock System ◽  
Mach Numbers ◽  
Measured Pressure

SummaryThis note presents the results of an experimental investigation of the flow over a simple delta wing designed for a Mach number of 3.5. Complete pressure distributions were measured for incidences of 0°, 10° and 20° at Mach numbers of 2.5 and 3.5. A number of schlieren photographs of the shock system around the wing were obtained at the same conditions and surface streamline patterns were studied at M = 3.5. The measurements were made to support numerical calculations which use this wing as a test case.

scholarly journals Detailed Experimental Studies of Flow in Large Scale Brush Seal Model and a Comparison With CFD Predictions

1999 ◽  
Author(s):  
L. H. Chen ◽  
P. E. Wood ◽  
T. V. Jones ◽  
J. W. Chew
Keyword(s):  
Large Scale ◽  
Experimental Studies ◽  
Flow Characteristics ◽  
Resistance Coefficient ◽  
Scale Model ◽  
Anisotropic Flow ◽  
Pressure Distributions ◽  
Brush Seal ◽  
Dimensional Parameters ◽  
Measured Pressure

A five times scale model of an engine brush seal has been manufactured. The bristle stiffness and pressure were chosen to satisfy close similarity of the relevant non-dimensional parameters, and the choice of parameters is described. The comparison of flow characteristics for the model seal and an engine seal confirmed the non-dimensional similarity. Detailed pressure measurements were performed within the bristle pack by employing hollow bristles. This novel measurement allowed insight to be obtained into the operation of both clearance and interference seals. In particular, the measured pressure variation in the region of the bristle tips was significant. The deflection of the bristles was determined by comparing the bristle tip pressures with the static pressures along the shaft. Hence the compaction of the pack in this region was found directly. A numerical modelling of brush seals employing anisotropic flow resistance has been developed. Predictions were compared with the measured pressure distributions within the pack. This enabled sensible selection of the pack resistance distribution to be made. Although uniform anisotropic resistance throughout the pack gave reasonable flow rate characteristics, the pressure distribution was not reproduced. A variation of resistance coefficient consistent with the observed compaction was required to give a solution comparable with the experiments.

Detailed Experimental Studies of Flow in Large Scale Brush Seal Model and a Comparison With CFD Predictions

2000 ◽  
Vol 122 (4) ◽  
pp. 672-679 ◽  
Author(s):  
L. H. Chen ◽  
P. E. Wood ◽  
T. V. Jones ◽  
J. W. Chew
Keyword(s):  
Large Scale ◽  
Experimental Studies ◽  
Flow Characteristics ◽  
Resistance Coefficient ◽  
Scale Model ◽  
Anisotropic Flow ◽  
Pressure Distributions ◽  
Brush Seal ◽  
Dimensional Parameters ◽  
Measured Pressure

A five times scale model of an engine brush seal has been manufactured. The bristle stiffness and pressure were chosen to satisfy close similarity of the relevant non-dimensional parameters, and the choice of parameters is described. The comparison of flow characteristics for the model seal and an engine seal confirmed the non-dimensional similarity. Detailed pressure measurements were performed within the bristle pack by employing hollow bristles. This novel measurement allowed insight to be obtained into the operation of both clearance and interference seals. In particular, the measured pressure variation in the region of the bristle tips was significant. The deflection of the bristles was determined by comparing the bristle tip pressures with the static pressures along the shaft. Hence the compaction of the pack in this region was found directly. A numerical modeling of brush seals employing anisotropic flow resistance has been developed. Predictions were compared with the measured pressure distributions within the pack. This enabled sensible selection of the pack resistance distribution to be made. Although uniform anisotropic resistance throughout the pack gave reasonable flow rate characteristics, the pressure distribution was not reproduced. A variation of resistance coefficient consistent with the observed compaction was required to give a solution comparable with the experiments. [S0742-4795(00)01703-8]

3D modelling of the flow distribution in the delta of Lake Øyeren, Norway

2010 ◽  
Vol 41 (2) ◽  
pp. 92-103 ◽  
Author(s):  
Peggy Zinke ◽  
Nils Reidar Bøe Olsen ◽  
Jim Bogen ◽  
Nils Rüther
Keyword(s):  
Water Level ◽  
Cross Sections ◽  
Stokes Equations ◽  
Morphological Changes ◽  
Flow Distribution ◽  
Field Measurements ◽  
Navier Stokes ◽  
Error Sources ◽  
Navier Stokes Equations ◽  
Water Level Measurements

A 3D numerical model was used to compute the discharge distribution in the channel branches of Lake Øyeren's delta in Norway. The model solved the Navier–Stokes equations with the k–ɛ turbulence model on a 3D unstructured grid. The bathymetry dataset for the modelling had to be combined from different data sources. The results for three different flow situations in 1996 and 1997 showed a relative accuracy of the computed discharges within the range of 0 to±20% compared with field measurements taken by an ADCP at 13 cross sections of the distributary channels. The factors introducing the most error in the computed results are believed to be uncertainties concerning the bathymetry. A comparison between the computational results of the older morphology data from 1985–1990 and the model morphology from 1995–2004 indicated that morphological changes in this period had already had consequences for the flow distribution in some channels. Other important error sources were the inevitable use of averaged water level gradients because of unavailable water level measurements within the delta.

On Transition From Supersonic to Subsonic Flow at Low Reynolds Numbers in a Tube

1969 ◽  
Vol 36 (2) ◽  
pp. 146-150 ◽  
Author(s):  
R. Y. Chen ◽  
J. C. Williams
Keyword(s):  
Mach Number ◽  
Static Pressure ◽  
Subsonic Flow ◽  
Supersonic Nozzle ◽  
Reynolds Numbers ◽  
Impact Pressure ◽  
Low Reynolds Numbers ◽  
Pressure Distributions ◽  
Low Reynolds ◽  
The Impact

A supersonic low-density gas stream produced in a supersonic nozzle was passed through a circular tube in which the transition from supersonic to subsonic flow took place. Static pressure distributions along the tube (and nozzle) and impact pressure distributions across the tube at several stations were measured to determine the nature of this transition. The impact pressure distributions were used, together with the local static pressure, to infer Mach number and velocity profiles in the tube. When the pressure distributions and center-line Mach number distributions are considered together, one obtains a fairly clear picture of the processes involved in the transition from supersonic to subsonic flow at low Reynolds numbers.

Numerical Simulation of Rocket Nozzle

2014 ◽  
Vol 984-985 ◽  
pp. 1210-1213
Author(s):  
G. Srinivas ◽  
Srinivasa Rao Potti
Keyword(s):  
Mach Number ◽  
Pressure Ratio ◽  
Divergence Angle ◽  
Performance Parameters ◽  
Ansys Fluent ◽  
Rocket Nozzle ◽  
The Public ◽  
Pressure Distributions ◽  
Fluent Software ◽  
Computational Fluid Dynamics Cfd

The vent or opening is called nozzle. The objectives are to measure the flow rates and pressure distributions within the converging and diverging nozzle under different exit and inlet pressure ratios. Analytic results will be used to contrast the measurements for the pressure and normal shock locations. In this paper computational Fluid Dynamics (CFD) Analysis of various performance parameters like static pressure, the Mach number, intensity of turbulence, the area ratio are studied in detail for a rocket nozzle from Inlet to exit by using Ansys Fluent software. From the public literature survey the geometry co-ordinates are taken. The throat diameter and exit and diameter are same for all nozzles. After the simulation the results revealed that the divergence angle varies the mach number and other performance parameters also varies. For smaller nozzle angle the discharge coefficient increases with increasing pressure ratio until the choked condition is reached for varying the divergence angle.

Comparison of Test and Analytical Results on CAP1400 Reactor Flow Distributor Designs

2017 ◽  
Author(s):  
Zhang Wei ◽  
Zhang Ming ◽  
Yu Hao ◽  
Yu Qing ◽  
Lin Shaoxuan
Keyword(s):  
Effective Means ◽  
Flow Distribution ◽  
Scale Model ◽  
Test Results ◽  
Hydraulic Test ◽  
Inlet Flow ◽  
The Core ◽  
Fuel Assemblies ◽  
Flow Distributor ◽  
Better Than

The CAP1400 reactor internal is going to use a new component termed the “Even Flow Distributor (EFD)”, instead of the existing flow skirt (FS) design, to help distribute the incoming flow more evenly to the fuel assemblies. To verify the effect of the EFD, a scale model of the reactor and internals was built and hydraulic tests of both the EFD and the FS configurations were conducted. In addition, numerical simulations of the flow fields, using CFD, of both designs were also carried out. From the scale model test results, the overall flow distribution of EFD is better than that of the FS. The core inlet flow distribution taken from the CFD results is slightly better than that from the hydraulic test. The differences between CFD result and test results are less than 3 percent for the most of fuel assemblies, and about 5 percent for a few assemblies. Based on this study, it is concluded that the EFD is a very effective means of controlling core inlet flow distribution in a CAP1400 reactor.

Flow Field of a Model Gas Turbine Swirl Burner

2012 ◽  
Vol 622-623 ◽  
pp. 1119-1124 ◽  
Author(s):  
Cheng Tung Chong ◽  
Simone Hochgreb
Keyword(s):  
Flow Field ◽  
Radial Velocity ◽  
Gas Turbine ◽  
Air Flow ◽  
Atmospheric Condition ◽  
Flow Fields ◽  
Swirl Flow ◽  
Scale Model ◽  
Swirl Burner ◽  
Swirling Air Flow

The flow field of a lab-scale model gas turbine swirl burner was characterised using particle imaging velocimetry (PIV) at atmospheric condition. The swirl burner consists of an axial swirler, a twin-fluid atomizer and a quartz tube as combustor wall. The main non-reacting swirling air flow without spray was compared to swirl flow with spray under unconfined and enclosed conditions. The introduction of liquid fuel spray changes the flow field of the main swirling air flow at the burner outlet where the radial velocity components are enhanced. Under reacting conditions, the enclosure generates a corner recirculation zone that intensifies the strength of the radial velocity. Comparison of the flow fields with a spray flame using diesel and palm biodiesel shows very similar flow fields. The flow field data can be used as validation target for swirl flame modelling.

Minimising Loss in a Heat Exchanger Installation for an Intercooled Turbofan Engine

2011 ◽  
Author(s):  
Pok-Wang Kwan ◽  
David R. H. Gillespie ◽  
Rory D. Stieger ◽  
Andrew M. Rolt
Keyword(s):  
Heat Exchanger ◽  
Cfd Simulation ◽  
Flow Distribution ◽  
Design Guidelines ◽  
Turbofan Engine ◽  
Aerodynamic Loss ◽  
Pressure Distributions ◽  
Cold Fluid ◽  
Core Concepts ◽  
Computational Fluid Dynamics Cfd

An intercooled turbofan engine has been proposed within NEWAC (New Aero Engine Core Concepts, an European Sixth Framework Programme) using lightweight heat exchangers. The requirement for compactness has led to the need for zigzag heat exchanger arrangement where the heat exchanger matrices are inclined to the cooling flows approaching them, but such an arrangement creates non-uniform mass flows through the cold fluid side intercooler ducting and the intercooler heat exchanger matrices. Design guidelines aimed at minimizing aerodynamic losses caused by the flow mal-distribution in such ducting is reported. Minimising the loss has the effect of optimising the heat transfer performance. Flow velocities and pressure distributions were measured experimentally in a simplified model of a heat exchanger and simulated in Computational Fluid Dynamics (CFD). Good agreement was found between measurement and predictions of the flow distribution in the cold fluid side intercooler ducting downstream of the heat exchanger matrices. A dominant jetting flow in the centre of each exit passage was identified as a source of aerodynamic loss. The CFD simulation has also shown that the main source of aerodynamic loss arises from the severe flow mal-distribution within the heat exchanger matrices. From these results, design guidelines are presented in this paper for the ducting, based on CFD studies on a series of simplified heat exchanger arrangement geometries.

Sign in / Sign up

Export Citation Format

Share Document