Analysis of Wireline Formation Test Data from Gas and Non-Darcy Flow Conditions

1999 ◽  
Vol 2 (02) ◽  
pp. 116-124
Author(s):  
Lee Jaedong

Summary Unlike liquid formation tests, in a gas formation test, both compressibility and viscosity vary with pressure, and non-Darcy flow is more likely. In this study, the gas formation rate analysis technique is developed to analyze gas pressure tests. We calculated gas pseudopotentials, utilized the geometric factor concept, and replaced Darcy's equation with Forchheimer's equation to study non-Darcy flow effects. The technique is applied to a field test, and the results are verified by history matching it with a three-dimensional near wellbore simulator. Introduction Wireline formation tests (WFT) can provide valuable, cost-effective information on undisturbed reservoir pressure (p*) vertical pressure gradients, formation fluid samples, formation fluid contacts, and an estimate of near-wellbore permeability. Various log responses (nuclear magnetic resonance, resistivity, acoustic) are calibrated with formation test permeabilities to obtain detailed permeability profiles.1,2 Permeability profiles are vital in identifying perforation and hydraulic fracturing intervals. Well-to-well correlation of permeability profiles can result in a lateral connectivity map, which can be used to calculate improved recovery efficiencies. A formation test is initiated when a probe from the tool is set against the formation. A measured volume of fluid is then withdrawn from the formation through the probe. The test continues with a buildup until the pressure stabilizes. Pressure in the tool is continuously monitored throughout the test. Historically, the cylindrical and the spherical flow analysis techniques are used to analyze wireline formation test data.3–5 An alternative to the conventional interpretation techniques has recently been developed by Kasap.6 In a recent publication, Kasap et al.7 compared conventional techniques with the formation rate analysis (FRA) technique and concluded that it was difficult to determine the spherical and the cylindrical flow periods for the conventional techniques that are applied to the buildup data only. The formation rate analysis technique combines the drawdown and the buildup data. Furthermore, early termination of the test would not hinder its analysis. Kasap et al.'s study was restricted to slightly compressible fluids, which is valid for testing liquid-saturated formations. For gases, however, both the compressibility and viscosity are strong functions of temperature and pressure and, thereby, variable during the test. Large gas compressibility and much smaller gas viscosity complicate the analysis. Gas flow because of low viscosity is more prone to non-Darcy flow effects. In this study, a new gas formation rate analysis (GFRA) technique is developed for gas formation testing. The technique calculates gas pseudopotentials and analyzes variation of pseudopotential versus formation rate during a formation test by utilizing the geometric factor concept. The technique is verified by history matching a field test with a three-dimensional (3D) near-wellbore simulation result. Analysis Technique The analysis technique is developed from the material balance considered for the volume of probe and flow lines. The mass rate of accumulation is equal to the difference between mass flow in from the formation and mass flow taken out by the pump. The mass flow rate in from the formation, pqf is defined; m f = ρ q f = M R T k G 0 r i L ∫ p ( t ) z μ d p , ( 1 ) where the density is substituted with an equation of state.8ri is the inner radius of the tool probe. G0 is the dimensionless geometric factor that accounts for flow geometry and is independent of flow rate, formation permeability, fluid viscosity, fluid type, and pressure drop in the system. A weak dependency to the wellbore radius can be ignored when the probe radius is about four times smaller than the wellbore radius. G0 also varies slightly with the probe radius. This variation, however, is not considered a drawback because the probe size of a formation test tool hardly changes. A one-time calculation of G0 is sufficient for a specific type of tool design. G0 is calculated from a numerical simulation of a specified formation test conducted with a specified tool. For the tests we analyzed, the probe size radius was 0.5 in., and the corresponding G0 was 4.27. We continue with the development of the analysis equations. The mass rate out from the tool is m d d = ρ q d d = p ( t ) M z R T q d d , ( 2 ) where ?qac is the pump drawdown rate. The mass rate of change or the accumulation rate, qdd in the tool is defined as m a c = ρ q a c = V s y s c t p ( t ) M z R T ∂ p ( t ) ∂ t , ( 3 ) where Vsys is the volume in the tool and ct is the compressibility of the fluid in the tool.

2021 ◽  
Vol 918 ◽  
Author(s):  
Daniel R. Lester ◽  
Marco Dentz ◽  
Aditya Bandopadhyay ◽  
Tanguy Le Borgne
Keyword(s):  

Abstract


2010 ◽  
Vol 132 (4) ◽  
Author(s):  
Yoon Jo Kim ◽  
Yogendra K. Joshi ◽  
Andrei G. Fedorov ◽  
Young-Joon Lee ◽  
Sung-Kyu Lim

It is now widely recognized that the three-dimensional (3D) system integration is a key enabling technology to achieve the performance needs of future microprocessor integrated circuits (ICs). To provide modular thermal management in 3D-stacked ICs, the interlayer microfluidic cooling scheme is adopted and analyzed in this study focusing on a single cooling layer performance. The effects of cooling mode (single-phase versus phase-change) and stack/layer geometry on thermal management performance are quantitatively analyzed, and implications on the through-silicon-via scaling and electrical interconnect congestion are discussed. Also, the thermal and hydraulic performance of several two-phase refrigerants is discussed in comparison with single-phase cooling. The results show that the large internal pressure and the pumping pressure drop are significant limiting factors, along with significant mass flow rate maldistribution due to the presence of hot-spots. Nevertheless, two-phase cooling using R123 and R245ca refrigerants yields superior performance to single-phase cooling for the hot-spot fluxes approaching ∼300 W/cm2. In general, a hybrid cooling scheme with a dedicated approach to the hot-spot thermal management should greatly improve the two-phase cooling system performance and reliability by enabling a cooling-load-matched thermal design and by suppressing the mass flow rate maldistribution within the cooling layer.


Author(s):  
Theodosios Korakianitis ◽  
Dequan Zou

This paper presents a new method to design (or analyze) subsonic or supersonic axial compressor and turbine stages and their three-dimensional velocity diagrams from hub to tip by solving the three-dimensional radial-momentum equation. Some previous methods (matrix through-flow based on the streamfunction approach) can not handle locally supersonic flows, and they are computationally intensive when they require the inversion of large matrices. Other previous methods (streamline curvature) require two nested iteration loops to provide a converged solution: an outside iteration loop for the mass-flow balance; and an inside iteration loop to solve the radial momentum equation at each flow station. The present method is of the streamline-curvature category. It still requires the iteration loop for the mass-flow balance, but the radial momentum equation at each flow station is solved using a one-pass numerical predictor-corrector technique, thus reducing the computational effort substantially. The method takes into account the axial slope of the streamlines. Main design characteristics such as the mass-flow rate, total properties at component inlet, hub-to-tip ratio at component inlet, total enthalpy change for each stage, and the expected efficiency of each streamline at each stage are inputs to the method. Other inputs are the radial position and axial velocity component at one surface of revolution through the axial stages. These can be provided for either the hub, or the mean, or the tip location of the blading. In addition the user specifies the azimuthal deflection of the flow from the axial direction at each radius (or as a function of radius) at each blade row inlet and outlet. By construction the method eliminates radial variations of total enthalpy (work) and entropy at each blade row inlet and outlet. In an alternative formulation enthalpy variations across radial positions at each axial station are included in the analysis. The remaining three-dimensional velocity diagrams from hub to tip, and the radial location of the remaining streamlines, are obtained by solving the momentum equation using a predictor-corrector method. Examples for one turbine and one compressor design are included.


2006 ◽  
Vol 129 (2) ◽  
pp. 212-220 ◽  
Author(s):  
Giovanna Barigozzi ◽  
Giuseppe Franchini ◽  
Antonio Perdichizzi

The present paper reports on the aerothermal performance of a nozzle vane cascade, with film-cooled end walls. The coolant is injected through four rows of cylindrical holes with conical expanded exits. Two end-wall geometries with different area ratios have been compared. Tests have been carried out at low speed (M=0.2), with coolant to mainstream mass flow ratio varied in the range 0.5–2.5%. Secondary flow assessment has been performed through three-dimensional (3D) aerodynamic measurements, by means of a miniaturized five-hole probe. Adiabatic effectiveness distributions have been determined by using the wide-band thermochromic liquid crystals technique. For both configurations and for all the blowing conditions, the coolant share among the four rows has been determined. The aerothermal performances of the cooled vane have been analyzed on the basis of secondary flow effects and laterally averaged effectiveness distributions; this analysis was carried out for different coolant mass flow ratios. It was found that the smaller area ratio provides better results in terms of 3D losses and secondary flow effects; the reason is that the higher momentum of the coolant flow is going to better reduce the secondary flow development. The increase of the fan-shaped hole area ratio gives rise to a better coolant lateral spreading, but appreciable improvements of the adiabatic effectiveness were detected only in some regions and for large injection rates.


2006 ◽  
Vol 2 (S237) ◽  
pp. 358-362
Author(s):  
M. K. Ryan Joung ◽  
Mordecai-Mark Mac Low

AbstractWe report on a study of interstellar turbulence driven by both correlated and isolated supernova explosions. We use three-dimensional hydrodynamic models of a vertically stratified interstellar medium run with the adaptive mesh refinement code Flash at a maximum resolution of 2 pc, with a grid size of 0.5 × 0.5 × 10 kpc. Cold dense clouds form even in the absence of self-gravity due to the collective action of thermal instability and supersonic turbulence. Studying these clouds, we show that it can be misleading to predict physical properties such as the star formation rate or the stellar initial mass function using numerical simulations that do not include self-gravity of the gas. Even if all the gas in turbulently Jeans unstable regions in our simulation is assumed to collapse and form stars in local freefall times, the resulting total collapse rate is significantly lower than the value consistent with the input supernova rate. The amount of mass available for collapse depends on scale, suggesting a simple translation from the density PDF to the stellar IMF may be questionable. Even though the supernova-driven turbulence does produce compressed clouds, it also opposes global collapse. The net effect of supernova-driven turbulence is to inhibit star formation globally by decreasing the amount of mass unstable to gravitational collapse.


2015 ◽  
Vol 54 (3) ◽  
pp. 605-623 ◽  
Author(s):  
Anthony C. Didlake ◽  
Gerald M. Heymsfield ◽  
Lin Tian ◽  
Stephen R. Guimond

AbstractThe coplane analysis technique for mapping the three-dimensional wind field of precipitating systems is applied to the NASA High-Altitude Wind and Rain Airborne Profiler (HIWRAP). HIWRAP is a dual-frequency Doppler radar system with two downward-pointing and conically scanning beams. The coplane technique interpolates radar measurements onto a natural coordinate frame, directly solves for two wind components, and integrates the mass continuity equation to retrieve the unobserved third wind component. This technique is tested using a model simulation of a hurricane and compared with a global optimization retrieval. The coplane method produced lower errors for the cross-track and vertical wind components, while the global optimization method produced lower errors for the along-track wind component. Cross-track and vertical wind errors were dependent upon the accuracy of the estimated boundary condition winds near the surface and at nadir, which were derived by making certain assumptions about the vertical velocity field. The coplane technique was then applied successfully to HIWRAP observations of Hurricane Ingrid (2013). Unlike the global optimization method, the coplane analysis allows for a transparent connection between the radar observations and specific analysis results. With this ability, small-scale features can be analyzed more adequately and erroneous radar measurements can be identified more easily.


Author(s):  
Liu Dian-Kui ◽  
Ji Le-Jian

The flow within a centrifugal rotor has strong characteristics of three-dimensional effect. A procedure called “stream-surface coordinates iteration” for the calculation of complete three dimensional flow in turbo-machinery is first described. Splitter blade techniques have been used in many rotors, especially in centrifugal compressors and pumps with high flow capacity. The difficulty of the calculation of the flow field for this type of rotor lies on that the mass flow ratio between the two sub-channels is unknown for the given total flow capacity. In the second part of this paper, an assumption about how to determine this mass flow ratio and a procedure to calculate the complete three-dimensional flow are presented. Finally, some design criteria about the splitter blades are put forward. Experimental data from two centrifugal pump impellers equipped with different splitter blades are also given to demonstrate the availability of the present calculation method.


Author(s):  
Yang Chen ◽  
Jun Li ◽  
Chaoyang Tian ◽  
Gangyun Zhong ◽  
Xiaoping Fan ◽  
...  

The aerodynamic performance of three-stage turbine with different types of leakage flows was experimentally and numerically studied in this paper. The leakage flows of three-stage turbine included the shroud seal leakage flow between the rotor blade tip and case, the diaphragm seal leakage flow between the stator blade diaphragm and shaft, as well as the shaft packing leakage flow and the gap leakage flow between the rotor blade curved fir-tree root and wheel disk. The total aerodynamic performance of three-stage turbine including leakage flows was firstly experimentally measured. The detailed flow field and aerodynamic performance were also numerically investigated using three-dimensional Reynolds-Averaged Navier-Stokes (RANS) and S-A turbulence model. The numerical mass flow rate and efficiency showed well agreement with experimental data. The effects of leakage flows between the fir-tree root and the wheel disk were studied. All leakage mass flow fractions, including the mass flow rate in each hole for all sets of root gaps were given for comparison. The effect of leakage flow on the aerodynamic performance of three-stage was illustrated and discussed.


Author(s):  
J. Paulon ◽  
C. Fradin ◽  
J. Poulain

Industrial pumps are generally used in a wide range of operating conditions from almost zero mass flow to mass flows larger than the design value. It has been often noted that the head-mass flow characteristic, at constant speed, presents a negative bump as the mass flow is somewhat smaller than the design mass flows. Flow and mechanical instabilities appear, which are unsafe for the facility. An experimental study has been undertaken in order to analyze and if possible to palliate these difficulties. A detailed flow analyzis has shown strong three dimensional effects and flow separations. From this better knowledge of the flow field, a particular device was designed and a strong attenuation of the negative bump was obtained.


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