Engineering topics

Pryor, D.

Publications and source records attributed to Pryor, D..

4 records

DOE OSTI2016

Decommissioning of the Reactor Pressure Vessels by Remote Controlled Thermal Cutting Segmentation Facilities of the ZION Nuclear Power Plant at ZION, USA - 16599

This paper presents the experiences for the segmentation of both reactor pressure vessels (RV) Units 1 and 2 at the ZION nuclear power plant. The Zion Station project was the first to use the large-scale application of thermal cutting (oxy-propane) technology in the USA. The elaborate planning and engineering was the basis for a quick, safe and flawless project execution without any aerosol migration or release of contamination. The used segmentation technology based on industry-tested methods with its big advantage of availability and spare parts inventory. For safeguarding Simulation (interfering edge analysis), animations and Trials with mock-ups dummies were executed prior. Also risk assessments and rescue concepts are part of the planning. Lean project organization for decommissioning and the flexibility, creativity, willingness to cooperate and willing for uninterrupted decisions of client and contractor are the essential basis for a successful project execution and a short project duration. The remote controlled segmentation of the RV of Unit 2 was performed in 3 month an in Unit 1 in less than 2 month.

12 MANAGEMENT OF RADIOACTIVE AND NON-RADIOACTIVE W↗

NASA NTRS1999

Development of a 12-Thrust Chamber Kerosene /Oxygen Primary Rocket Sub-System for an Early (1964) Air-Augmented Rocket Ground-Test System

Airbreathing/Rocket combined-cycle, and specifically rocket-based combined- cycle (RBCC), propulsion systems, typically employ an internal engine flow-path installed primary rocket subsystem. To achieve acceptably short mixing lengths in effecting the "air augmentation" process, a large rocket-exhaust/air interfacial mixing surface is needed. This leads, in some engine design concepts, to a "cluster" of small rocket units, suitably arrayed in the flowpath. To support an early (1964) subscale ground-test of a specific RBCC concept, such a 12-rocket cluster was developed by NASA's Marshall Space Flight Center (MSFC). The small primary rockets used in the cluster assembly were modified versions of an existing small kerosene/oxygen water-cooled rocket engine unit routinely tested at MSFC. Following individual thrust-chamber tests and overall subsystem qualification testing, the cluster assembly was installed at the U. S. Air Force's Arnold Engineering Development Center (AEDC) for RBCC systems testing. (The results of the special air-augmented rocket testing are not covered here.) While this project was eventually successfully completed, a number of hardware integration problems were met, leading to catastrophic thrust chamber failures. The principal "lessons learned" in conducting this early primary rocket subsystem experimental effort are documented here as a basic knowledge-base contribution for the benefit of today's RBCC research and development community.

Pryor, D.↗

NASA NTRS1986

Remote access for NAS: Supercomputing in a university environment

The experiment was designed to assist the Numerical Aerodynamic Simulation (NAS) Project Office in the testing and evaluation of long haul communications for remote users. The objectives of this work were to: (1) use foreign workstations to remotely access the NAS system; (2) provide NAS with a link to a large university-based computing facility which can serve as a model for a regional node of the Long-Haul Communications Subsystem (LHCS); and (3) provide a tail circuit to the University of Colorado a Boulder thereby simulating the complete communications path from NAS through a regional node to an end-user.

Johnson, G.↗

NASA NTRS1972

Extendible rocket nozzle development

An evaluation is presented of J-2 engine modifications that will simplify operation and improve reliability of the advanced Saturn 1C launch vehicle. Methods of increasing thrust without extensively modifying the S-2 or S-4B stages are also evaluated. A thrust increase was achieved by raising engine combustion through a redesign of the engine thrust chamber and propellant feed system.

Pryor, D.↗