Qualification test results, 5 lb/f/ /22 Newton/ earth storable bipropellant rocket engine

1981 ◽  
Author(s):  
R. STECHMAN ◽  
C. DRENNING
Keyword(s):  
Rocket Engine ◽  
Test Results ◽  
Qualification Test

scholarly journals Qualification test results for the TIRS cryocooler

2012 ◽  
Author(s):  
Eric Marquardt ◽  
Wilfred Gully ◽  
Jennifer Marquardt ◽  
Robert Boyle ◽  
Taylor Hale
Keyword(s):  
Test Results ◽  
Qualification Test

Measurements of Rotordynamic Coefficients of Hybrid Bearings With (a) a Plugged Orifice, and (b) a Worn Land Surface

2002 ◽  
Vol 124 (2) ◽  
pp. 363-368 ◽  
Author(s):  
F. Laurant ◽  
D. W. Childs
Keyword(s):  
Test Data ◽  
Land Surface ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Test Results ◽  
Rotordynamic Coefficients ◽  
Hybrid Bearing ◽  
Liquid Rocket

Test results are presented for the rotordynamic coefficients of a hybrid bearing that is representative of bearings for liquid-rocket-engine turbopump applications. The bearing is tested in the following two degraded conditions: (a) one of five orifices plugged, and (b) a locally enlarged clearance to simulate a worn condition. Test data are presented at 24,600 rpm, with supply pressures of 4.0, 5.5, and 7.0 MPa, and eccentricity ratios from 0.1 to 0.5 in 0.1 increments. Overall, the results suggest that neither a single plugged orifice nor significant wear on the bearing land will “disable” a well-designed hybrid bearing. These results do not speak to multiple plugged orifices and are not an endorsement for operations without filters to prevent plugging orifices.

Design and Testing of ITER TF Coil Insulations

2011 ◽  
Vol 21 (3) ◽  
pp. 3127-3131 ◽  
Author(s):  
Matthew W. Hooker ◽  
Jennifer K. Walsh ◽  
Mark W. Haynes ◽  
Naseem A. Munshi
Keyword(s):  
Radiation Exposure ◽  
Large Scale ◽  
Mechanical Performance ◽  
International Organization ◽  
Vacuum Impregnation ◽  
Test Results ◽  
Qualification Test ◽  
Insulation System ◽  
Cyanate Ester Resin ◽  
Design And Testing

The design of the ITER Toroidal Field (TF) coils requires an insulation system that is amenable to the very large scale vacuum impregnation processes planned for the construction of these devices, and that will provide reliable electro-mechanical performance after radiation exposure. To address this need, CTD has developed an epoxy/cyanate ester resin system designated CTD-425. This material meets the processing requirements for use in the TF coils, and cyclic mechanical testing of conductor assemblies has demonstrated its electro-mechanical strength after 60,000 mechanical cycles. In addition, this product recently passed radiation exposure tests coordinated by the ITER International Organization and is now qualified for use in constructing the TF coils. This paper summarizes the performance characterization and qualification test results for this insulation.

Transient Lift-Off Test Results for an Experimental Hybrid Bearing in Air, Simulating a Liquid Hydrogen Turbopump Start Transient

2016 ◽  
Author(s):  
Dara W. Childs ◽  
David Klooster ◽  
Henry Borchard ◽  
Dustin Pavelek ◽  
Stephen Phillips
Keyword(s):  
Rocket Engine ◽  
Transient Behavior ◽  
Simulation Software ◽  
Test Results ◽  
Unit Load ◽  
Ramp Rate ◽  
Fluid Medium ◽  
Supply Pressure ◽  
Lift Off ◽  
Point Of Departure

Start-transient testing of a hybrid (combined hydrostatic and hydrodynamic action) bearing supplied with air was completed, providing an indication of its performance while operating in a compressible fluid medium. The test start transients were modeled after Rocket Engine Transient Simulation Software (ROCETS) predictions for start-transient behavior of running speed ω(t) and bearing supply pressure Ps(t). The top test speed was 15 krpm. The ramp rate, supply pressure Ps values at 15 krpm, constant bearing unit load magnitude w0, and load orientation (load-on-recess LOR or load-on-land LOL) were varied. Five different load-case combinations were carried out (separately) for LOR and LOL load configurations with ramp rates varying from 2206 rpm/s to 8824 rpm/s. The target pressures at 15 krpm varied from 5.32 bars to 18.25 bars. The tested bearing dimensions were: L = D = 38.1 mm, and Cr =.0635 mm. Lift-off occurs due to the increase in Ps (ω dependent) and was defined as the point of departure towards the center of the bearing with increasing ω while the rotor remained 0.00254 mm (0.1 mils) above the bearing surface. This method is limited by the inability to accurately measure an established operating bearing clearance. Evaluation of the lift-off Ps versus applied unit load w0 supports the following conclusions: (1) Lift-off Ps is approximately a linear function of w0, (2) Changing the ramp rate while keeping constant the specified Ps at 15 krpm has no significant impact, (3) Lowering the limit Ps at 15 krpm may reduce the lift-off Ps value, and (4) The LOR start-transient cases required a higher lift-off speed and lift-off Ps values than the corresponding LOL start-transient cases.

Advanced cryogenic solid hybrid rocket engine developments - Concept and test results

1998 ◽  
Author(s):  
Christopher St. Clair ◽  
Daniel Gramer ◽  
Eric Rice ◽  
William Knuth
Keyword(s):  
Rocket Engine ◽  
Test Results ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

Performance of Small High Speed Cryogenic Pumps

1985 ◽  
Vol 107 (2) ◽  
pp. 197-203 ◽  
Author(s):  
Kenjiro Kamijo ◽  
Kunio Hirata
Keyword(s):  
High Speed ◽  
Rocket Engine ◽  
Pump Efficiency ◽  
Test Results ◽  
Flow Rates ◽  
High Head ◽  
Design Characteristics ◽  
Liquid Rocket ◽  
Reported Data ◽  
The Relationship

Several small cryogenic pumps for a liquid rocket engine have been made and tested. These pumps have a small impeller and are characterized by high speed and high head. The main design characteristics of these pumps are as follows: stage specific speeds of from 0.0319 to 0.0766, flow rates from 0.016 to 0.0525 m3/s, pressure rises from 4.9 to 26 MPa, rotational speeds from 16,500 to 80,000 rpm, and impeller diameters from 0.083 to 0.146 m. These pumps, when tested, showed higher efficiency even in the range of small stage specific speeds than any previously reported data on other pumps. This tendency was particularly striking with the two-stage pumps. With regard to pump efficiency measurement, it was made clear that adiabatic efficiency was utilizable for the present cryogenic pumps. The relationship between the adiabatic efficiency and ordinary efficiency was also confirmed by a brief calculation and test results.

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