October 27, 2011
History Dr. Richard Passamaneck- Inventor •BS & MS Engineering UCLA •PhD Aerospace Engineering USC •11 Years NASA Jet Propulsion Lab •Propulsion research utilizing solid rocket propellants •1982 Colorado School of Mines •Joint research with Dr. James Crafton Professor of Petroleum Engineering •Propellant research & ignition patent
PFS ’ Approach
Propellant Optimize Energy and Work on Formation • Known Burn Geometry/Ignition System • Known Propellant Characteristics; • Higher Energy/Longer Burn Durations; • Verified Results
Geometry Known Burn Geometry via Ignition External Ignition Internal Ignition Deflagration - Known Geometry Detonation - Unknown Geometry
PFS ’ Propellants: Overview
Propellant Propellant Selection Criteria • Produces gas at a specific burn rate to cause fractures without transitioning to a harmful detonation; • High energy content available to do work on formation released over sufficient time to extend fractures; • Sufficient total gas volume production to produce and extend fractures significantly into the formation; Stable propellant with minimal “ knee ” to assure no transition to detonation • and safe deployment; • Environmentally safe with no combustion products which may be harmful to the formation; • Ignition not pressure limited . Normal well bore temperatures do not effect propellant performance
Team
Team •Worlds largest producer of tactical rocket motors and propellants: -Sidewinder, Tomahawk, Patriot & Stinger Missiles Systems •Built Bomb Calorimeter and Strand-Burners for testing •Exclusive Agreement with Aerojet
Propellant Volumetric Energy Comparison a 3-D Column 1 Octane StimGun Propellant PFS Arcite Propellant PFS Arcadene Propellant Tovite (TNT Substitute)
Propellant Per Shot Energy Comparison 3-D Column 1 Octane Common Oil & Gas Industry Prop PFS Arcadene Propellant
Propellant Characteristics - How It Burns
Typical Burn Curve 4 Burn Rate vs. Pressure Measured Data and for Arcite 386M Propellant Muraour's Law Model r = -0.610 + 3.050E-04 p 3 Burn Rate - in/sec 2 Ballistic Burn Model r = 0.04004 p^0.42 1 0 0 3500 7000 10500 14000 Pressure - psi
Propellant 18 Burn Rate Comparison Ballistic Burn Rat e Model 16 R = 0.003 p 0.9 14 StressFrac R=0.041p 0.7 12 Knee? 10 in/sec Burn Rate StimGun 8 Knee? 6 Measured Data and Muraour’s Law Model R = -0.610 + 3.050E-4 p 4 Ballistic Burn Rate Model Ballistic Burn Rate Model ARCite Arcite 386M 2 R = 0.04004 p ^ 0.42 R = 0.04004 p 0.42 Knee 0 0 00 00 00 000 00 00 00 00 20 40 60 8 100 120 140 160 Pr essure - psi
Technical Overview HOW DO WE ACHIEVE BETTER PROPELLANT TREATMENTS? OVERVIEW OF WORK CONCEPTS • “ Best ” Pressure Pulse • Comparative Work Graph
Technical Overview
Technical Overview
Technical Overview
Technical Overview
Alamien HSW-2 Frac Gradient 0.7 psi/ft 460 msec Frac Pressure ~4480psi
Gauge Data Downhole Pressure Gauge Data – North Sea Well 300 msecs Frac Pressure ~ 7,000 psi
Technical Overview OPTIMIZING TREATMENTS: GENERATION II • Higher Burn Rates • Increased Gas Generation or Output • Quicker Pressure Rise Times to Initiate Fractures • Higher Peak Pressures/Long Duration to “ Optimize ” Work • Maintain Predictability and Repeatability (No Explosion)
Technical Overview Burn Rate versus Pressure 12 Arcite 386M Arcite 497 Arcadene 454A Arcadene 439 9 Burn Rate 6 3 0 1000 3000 5000 7000 9000 11000 13000 Pressure
Technical Overview Theoretical Relative Gas Volume Generation (Compared to Arcite 386M Baseline) 400.00% 300.00% Percentage Comparison Arcite 386M Arcite 497 Arcadene 454A 200.00% Arcadene 439 100.00% 0.00% 1000 3000 5000 7000 9000 11000 13000 Pressure
Technical Review PVI
Technical Overview “Soft” Ignition Test with Electric Match One End Only
Technical Overview Detonating Cord Ignition Test – Full Length Propellant
ControlFrac TM •Multiple Applications •Customized Burn Curves Propellant Cartridge (Mixed to Optimize) •TCP, WL, CT, Slickline •Horizontal/Vertical Gas Ports •Varying Propellant Mix
PERFORATING GUN ENHANCEMENT
Technical Oveview PERFORATING GUN ENHANCEMENT • Challenges: Propellant Damaging Guns • Propellant Design Concepts • Effects of Slope Break (Knee) • Choosing the Right Propellant • Correct Ignition • Patented Solution - Control
Technical Overview CHALLENGES: VIEWING THE VIDEO ON THE NEXT SLIDE, YOU WILL NOTE THAT WHEN PROPELLANT IS BURNED INSIDE A CLOSED VESSEL, IF THE WRONG PROPELLANT IS USED, OR IF IT IS INCORRECTLY CONFIGURED, A DETONATION WILL OCCUR, DESTROYING THE VESSEL.
Technical Overview Video Detailing Detonating Perf Gun Mock Up (Double Click to Start Video)
Technical Overview GOAL: HOW DO WE PUT PROPELLANT IN A CLOSED VESSEL WITHOUT RUPTURE?
Technical Review SOLUTION: CONTROL PRESSURE BY KNOWING PROPELLANT CHARACTERISTICS AND APPLYING KNOWN PROPELLANT DESIGN CONCEPTS At = (As x r x ρ x Cstar)/(p x g) The total aperture area (At) to achieve a desired pressure (p), can be related by taking into account propellant characteristic variables, namely: (1) the burning surface area of the propellant (As); (2) the burn rate characteristics of the propellant, more specifically, the burn rate as a function of pressure (r); (3) the density of the propellant ( ρ ); (4) the characteristic velocity of the propellant (Cstar); and (5) the gravitational constant (g)
Technical Review HOW DO WE APPLY THIS TO PERFORATING GUNS?
Technical Review • IN A PERFORATING GUN, THE FLOW AREA, At, IS FIXED. IT IS THE TOTAL AREA CREATED BY THE PERFORATING CHARGES; • AS THIS FLOW AREA IS REDUCED FOR A CONSTANT PROPELLANT TYPE AND GEOMETRY, THE PRESSURE INSIDE THE GUN INCREASES; • BECAUSE THE BURN RATE SLOPE CHANGES AT THE “KNEE”, RUNAWAY DEFLAGRATION OCCURS IF PRESSURES ABOVE THE KNEE DEVELOP WITHIN THE VESSEL, DAMAGING THE VESSEL; • THIS RUNAWAY DETONATION OCCURS AS THE GUN PRESSURES APPROACH THE PROPELLANT SLOPE BREAK OR “KNEE” (SEE FOLLOWING SLIDE).
Technical Review Gauge Data from Aperture Control Vessel Test Arcite 386M At Slope Break Pressure, Transitions to Detonation
Propellant 4 Burn Rate vs. Pressure Measured Data and for Arcite 386M Propellant Muraour's Law Model r = -0.610 + 3.050E-04 p 3 Burn Rate - in/sec 2 Ballistic Burn Model r = 0.04004 p^0.42 1 Slope Break Pressure 0 0 3500 7000 10500 14000 Pressure - psi
Technical Review • A PROPELLANT WITH A SLOPE BREAK WELL IN EXCESS OF THE MAXIMUM SAFE PRESSURE WITHIN THE GUN ALLOWS THE TOTAL BURN EVENT TO TAKE PLACE ALONG THE CONSTANT BURN SLOPE PORTION OF THE BURN RATE CURVE; • A PROPELLANT SUCH AS ARCADENE 439 HAS A HIGH PRESSURE SLOPE BREAK, MAKING IT AN IDEAL CANDIDATE TO BE USED IN A CLOSED VESSEL SUCH AS A PERFORATING GUN WHERE HIGHER MAXIMUM PRESSURES ARE REQUIRED (NOTE THE BURN RATE CURVES ON THE FOLLOWING SLIDE)
Technical Review Burn Rate versus Pressure 12 Arcite 386M Arcite 497 Arcadene 454A Arcadene 439 9 Burn Rate 6 3 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 1200013000 14000 Pressure
Technical Review In Summary, THE SOLUTION : The propellant characteristics and geometry can be used to safely achieve desired pressures within a vessel or perforating gun without exceeding the vessel’s maximum allowable stresses, without reducing the total energy by limiting propellant mass inside the gun ; and Knowing the total flow area, or size and number of shots per foot in a perforating gun, and deploying the correct propellant, safe and predictable peak pressures can be achieved within a perforating gun that do not result in gun damage.
Technical Overview SOLUTION: VIEWING THE VIDEOS ON THE NEXT TWO SLIDES, YOU WILL NOTE THAT WHEN THE PROPER PROPELLANT IS USED INSIDE A CLOSED VESSEL OR PERFORATING GUN, A CONTROLLED DEFLAGRATION PRODUCING A DESIRED PRESSURE PULSE IS ACHIEVED.
Technical Review Video I Detailing Safe Burn in Perf Gun Mock Up (Approximately 30 second duration)
Technical Review Video II Detailing Safe Burn in Perf Gun Mock Up
Technical Review Video III Perforating with Propellant Mock Up
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