Computer programs for the design of liquid-to-liquid jet pumps

Computer programs based on one-dimensional equations for cavitating and noncavitating flow in liquid-to-liquid jet pumps are described

Comparison of calculated and experimental cascade performance for controlled-diffusion compressor stator blading

The mid-span section of a previously reported controlled-diffusion compressor stator has been experimentally evaluated in cascade. Measurements are taken over a range of incidence angles for blade chord Reynolds numbers from 470,000 to 690,000. Blade chord length is 12.7 cm, aspect ratio is 2.0, and solidity is 1.67. Measurements include conventional cascade performance parameters as well as blade surface pressures. Computations are made for the inviscid flow field, surface boundary layers, and loss for several of the blade inlet angle conditions, are compared against corresponding data

The effect of circumferential distortion on fan performance at two levels of blade loading

Single stage fans designed for two levels of pressure ratio or blade loading were subjected to screen-induced circumferential distortions of 90-degree extent. Both fan rotors were designed for a blade tip speed of 425 m/sec, blade solidity of 1.3 and a hub-to-tip radius ratio of 0.5. Circumferential measurements of total pressure, temperature, static pressure, and flow angle were obtained at the hub, mean and tip radii at five axial stations. Rotor loading level did not appear to have a significant influence on rotor response to distorted flow. Losses in overall pressure ratio due to distortion were most severe in the stator hub region of the more highly loaded stage. At the near stall operating condition tip and hub regions of (either) rotor demonstrated different response characteristics to the distorted flow. No effect of loading was apparent on interactions between rotor and upstream distorted flow fields

Some observations of the effects of radial distortions on performance of a transonic rotating blade row

A single rotating blade row was tested with two magnitudes of tip radial distortion and two magnitudes of hub radial distortion imposed on the inlet flow. The rotor was about 50 centimeters (20 in.) in diameter and had a design operating tip speed of approximately 420 meters per second (1380 ft/sec). Overall performance at 60, 80, and 100 percent of equivalent design speed generally showed a decrease (compared to undistorted flow) in rotor stall margin with tip radial distortion but no change, or a slight increase, in rotor stall margin with hub radial distortion. At design speed there was a decrease in rotor overall total pressure ratio and choke flow with all inlet flow distortions. Radial distributions of blade element parameters are presented for selected operating conditions at design speed

What Effect Do Athletic Facilities Have on Recruitment of Division I Athletes?

Context: Recruiting elite athletes to commit to a university athletic program is paramount in the success of any athletic department; in turn this has the potential to increase overall revenue and notoriety to the institution. Athletic facilities may have a significant role on an athlete’s selection process. Objective: To examine the impact sporting facilities have on the recruitment of Division I athletes. Design: Cross-sectional, descriptive study. Setting: Division I athletic program. Participants: 67 varsity athletes from 14 different teams. Intervention: A descriptive survey instrument was developed to identify the athlete’s top ten reasons they chose to attend/play for BGSU. Popular reasons listed were based on top five results of previous research. Main Outcome Measures: Dependent variables (athlete’s rankings about and identification on why they selected their current institution), included nominal data choices (i.e., male/female, scholarship status, etc.). Results: Most important college choice factors from the whole group are: (1) head coach personality/philosophy, (2) degree options, (3) size of the university, (4) academic support services, (5) sporting facilities, (6) location of the university, (7) perceived opportunity to play immediately, (8) financial aid, (9) traditions and (10) perceived future playing opportunities. An independent t-test was used to examine differences between male’s and female’s rank of facilities. Males (n=9) had a M=6.44±1.87. Females (n=28) had a M=5.14±2.04. One-way ANOVA was used to examine differences between the academic level of the athletes and where they ranked facilities in their top ten. Freshman (n=15) had a M=5.40±1.72. Sophomores (n=7) had a M=5.85±2.03. Juniors (n=4) had a M=6.50±1.73. Seniors (n=8) had a M=5.37±2.87. Graduate students (n=2) had a M=3.00±1.41. Cronbach’s α=.712 for this survey. Conclusion: The data reiterates the importance of having the best facilities possible in order to attract the best athletic talent to your institution. Practical Application: Recognizing there are many reasons athletes choose a university can better prepare athletic departments to recruit future athletes. By examining the reasons Division I athletes chose to play for a university we can expand our understanding of how young athletes prioritize important life choices

Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques

A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory. The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio (1.2) rotor has been designed for a specific head ratio of .25 and a tip relative inlet Mach number of 1.3. Overall stage pressure ratio is 1.56. The rotor was designed using an Euler code augmented by a distributed body force model to account for viscous effects. This provided a relatively quick-running design tool, and was used for both rotor and stator calculations. The initial stator sections were sized using a compressible, cascade panel code. In addition to being used as a case study for teaching purposes, the compressor stage will be used as a research stage. Detailed measurements, including non-intrusive LDV, will be compared with the design computations, and with the results of other CFD codes, as a means of assessing and improving the computational codes as design tools

Performance of a 1.57 pressure-ratio transonic fan stage with a screen-induced 90 deg circumferential inlet flow distortion

A transonic fan stage having a design pressure ratio of 1.57 was tested with a 90 degree circumferential distortion imposed on the inlet flow. The rotor diameter was approximately 50.8 cm, and the design pressure ratio was 1.60 at a tip speed of 425 m/sec. Overall performance at 70 and 100 percent of design speed showed a loss of stall pressure ratio and flow range at design speed and no significant loss in stall pressure ratio at 70 percent of design speed. Detailed flow measurements are presented to show the rotor-upstream flow interactions and the attenuation and amplification properties through the stage

Two-dimensional analytical and experimental performance comparison for a compressor stator section with D-factor of 0.47

Analytically computed flow parameters were compared to measured values for the midspan double-circular-arc section of a stator in subsonic flow. Analytical procedures included calculations for inviscid flow, blade surface boundary layers, and loss coefficients. Comparisons were made at three incidence angles. Methods for prescribing the exit fluid angle in inviscid flow calculations were investigated. Measured loss coefficients were compared to calculated values. Two methods for predicting performance involving iterative use of ideal flow and boundary layer calculations were investigated

A Workshop to Incorporate Language Development in Teaching Reading

It is the purpose of this paper to describe a workshop designed to teach elementary school teachers how to incorporate language development activities during reading instruction, particularly with children who have language-based reading difficulties