October 27, 2011 History Dr. Richard Passamaneck- Inventor BS - - PowerPoint PPT Presentation

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October 27, 2011 History Dr. Richard Passamaneck- Inventor BS - - PowerPoint PPT Presentation

Feb 04, 2023 168 likes •652 views

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

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October 27, 2011

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  • 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

History

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SLIDE 3

PFS’ Approach

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SLIDE 4

Optimize Energy and Work on Formation

  • Known Burn Geometry/Ignition System
  • Known Propellant Characteristics;
  • Higher Energy/Longer Burn Durations;
  • Verified Results

Propellant

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SLIDE 5

Geometry

Known Burn Geometry via Ignition External Ignition

Deflagration - Known Geometry

Internal Ignition

Detonation - Unknown Geometry

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SLIDE 6

PFS’ Propellants: Overview

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SLIDE 7

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

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SLIDE 8

Team

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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
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SLIDE 10

a

3-D Column 1 Octane StimGun Propellant PFS Arcite Propellant PFS Arcadene Propellant Tovite (TNT Substitute)

Volumetric Energy Comparison

Propellant

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SLIDE 11

Propellant

Per Shot Energy Comparison

3-D Column 1 Octane Common Oil & Gas Industry Prop PFS Arcadene Propellant

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Propellant Characteristics - How It Burns

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Burn Rate - in/sec

1 2 3 4

Pressure - psi

3500 7000 10500 14000

Burn Rate vs. Pressure for Arcite 386M Propellant

Ballistic Burn Model r = 0.04004 p^0.42 Measured Data and Muraour's Law Model r = -0.610 + 3.050E-04 p

Typical Burn Curve

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SLIDE 14

Propellant

ARCite 386M Ballistic Burn Rate Model R = 0.04004 p ^ 0.42

2 4 6 8 10 12 14 16 18 20 00 40 00 60 00 8 000 100 00 120 00 140 00 160 00

Pr essure - psi

Ballistic Burn Rat e Model R = 0.003 p 0.9 Measured Data and Muraour’s Law Model R = -0.610 + 3.050E-4 p StimGun Arcite Ballistic Burn Rate Model R = 0.04004 p 0.42 Burn Rate Comparison

Burn Rate in/sec

Knee? Knee

StressFrac R=0.041p0.7

Knee?

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Technical Overview

HOW DO WE ACHIEVE BETTER PROPELLANT TREATMENTS? OVERVIEW OF WORK CONCEPTS

  • “Best” Pressure Pulse
  • Comparative Work Graph
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Technical Overview

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SLIDE 17

Technical Overview

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SLIDE 18

Technical Overview

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SLIDE 19

Technical Overview

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Alamien HSW-2

Frac Gradient 0.7 psi/ft Frac Pressure ~4480psi 460 msec

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SLIDE 21

Gauge Data

Downhole Pressure Gauge Data – North Sea Well Frac Pressure ~ 7,000 psi 300 msecs

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SLIDE 22

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)
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SLIDE 23

Technical Overview

Burn Rate versus Pressure Burn Rate

3 6 9 12

Pressure

1000 3000 5000 7000 9000 11000 13000 Arcite 386M Arcite 497 Arcadene 454A Arcadene 439

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SLIDE 24

Technical Overview

Theoretical Relative Gas Volume Generation (Compared to Arcite 386M Baseline)

Percentage Comparison 0.00% 100.00% 200.00% 300.00% 400.00% Pressure 1000 3000 5000 7000 9000 11000 13000 Arcite 386M Arcite 497 Arcadene 454A Arcadene 439

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Technical Review

PVI

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Technical Overview

“Soft” Ignition Test with Electric Match One End Only

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SLIDE 27

Technical Overview

Detonating Cord Ignition Test – Full Length Propellant

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ControlFracTM

Propellant Cartridge (Mixed to Optimize)

  • Multiple Applications
  • Customized Burn Curves
  • TCP, WL, CT, Slickline
  • Horizontal/Vertical
  • Varying Propellant Mix

Gas Ports

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SLIDE 29

PERFORATING GUN ENHANCEMENT

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SLIDE 30

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
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SLIDE 31

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.

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SLIDE 32

Technical Overview

Video Detailing Detonating Perf Gun Mock Up (Double Click to Start Video)

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SLIDE 33

Technical Overview

GOAL: HOW DO WE PUT PROPELLANT IN A CLOSED VESSEL WITHOUT RUPTURE?

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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)

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Technical Review

HOW DO WE APPLY THIS TO PERFORATING GUNS?

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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).

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SLIDE 37

Technical Review

Gauge Data from Aperture Control Vessel Test

Arcite 386M At Slope Break Pressure, Transitions to Detonation

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SLIDE 38

Burn Rate - in/sec

1 2 3 4

Pressure - psi

3500 7000 10500 14000

Burn Rate vs. Pressure for Arcite 386M Propellant

Ballistic Burn Model r = 0.04004 p^0.42 Measured Data and Muraour's Law Model r = -0.610 + 3.050E-04 p

Propellant

Slope Break Pressure

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SLIDE 39

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)

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SLIDE 40

Technical Review

Burn Rate versus Pressure

Burn Rate 3 6 9 12 Pressure 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 1200013000 14000 Arcite 386M Arcite 497 Arcadene 454A Arcadene 439

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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.

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SLIDE 42

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.

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SLIDE 43

Technical Review

Video I Detailing Safe Burn in Perf Gun Mock Up (Approximately 30 second duration)

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Technical Review

Video II Detailing Safe Burn in Perf Gun Mock Up

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Technical Review

Video III Perforating with Propellant Mock Up

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Pressure Modeling

8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40

UNITS PRESSURE PSI 5000 6000 7000 8000 9000 10000 12000 14000 16000 18000 20000 Natural Log of Pressure

  • 8.5172

8.6995 8.8537 8.9872 9.1050 9.2103 9.3927 9.5468 9.6803 9.7981 9.903 DO NOT CALCULATE PRESSURES BEYOND: 25000 PSIG BURN INSIDE TO OUTSIDE INCLUDE END AREA N ID IN 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25 0.25 LENGTH (Enter 0 if no inside burn) IN 26.82 28.72 30.42 31.95 33.37 34.7 37.1 39.25 41.2 42.98 44.65 INSIDE SURFACE AREA IN^2 21.064 21.064379 21.064379 21.064379 21.064379 21.064379 21.064379 21.064379 21.064379 21.064379 21.064379 BURN OUTSIDE to Inside INCLUDE END AREA N OD IN 2 2 2 2 2 2 2 2 2 2 2 LENGTH (Enter 0 if no outside burn) IN 26.82 28.72 30.42 31.95 33.37 34.7 37.1 39.25 41.2 42.98 44.65 OUTSIDE SURFACE AREA IN^2 168.515 180.453 191.134 200.748 209.670 218.027 233.106 246.615 258.867 270.051 280.544

TOTAL AREA for INSIDE and OUTSIDE

IN^2 189.579 201.517 212.199 221.812 230.734 239.091 254.171 267.679 279.932 291.116 301.609 Total Length IN 26.82 28.72 30.42 31.95 33.37 34.7 37.1 39.25 41.2 42.98 44.65 Total Propellant Volume IN^3 82.941 88.817 94.074 98.806 103.197 107.310 114.732 121.381 127.411 132.916 138.080 ρ - Density LB/FT^3 0.0602 0.060 0.060 0.060 0.060 0.060 0.060 0.060 0.060 0.060 0.060 Cstr (constant) FT/SEC 4634 4634 4634 4634 4634 4634 4634 4634 4634 4634 4634 gc (gravitational constant) - FT LB/LBF SEC^2 32.174 32.174 32.174 32.174 32.174 32.174 32.174 32.174 32.174 32.174 32.174 Burn Rate IN/SEC 5.7656 6.5088 7.2114 7.8811 8.5232 9.1418 10.3201 11.4342 12.4960 13.5141 14.4949 Exponent

  • 0.6672

0.7475 0.8155 0.8743 0.9262 0.9727 1.0530 1.1210 1.1798 1.2317 1.2782 N/A 7500 PSIG PROP TYPE ( 1, 2 or 3) 3 ARCADENE 439 At - Calculated Throat Area IN^2 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 0.0316 Discharge Coefficient:

  • 0.643

0.643 0.643 0.643 0.643 0.643 0.643 0.643 0.643 0.643 0.643 Actual Throat Area IN^2 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 0.0491 Burn Time SEC 0.1734 0.1536 0.1387 0.1269 0.1173 0.1094 0.0969 0.0875 0.0800 0.0740 0.0690 dP/dAt

  • 3429482

3326170.8 3240607.7 3169204.1 3106094 3049526.2 2954679 2876025.3 2809468.6 2752562.9 2701406.7 ORIFICE DIAMETER for 60 ORIFICES IN 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 NUMBER OF ORIFICES 60 AREA OF PROPELLANT BURNING PROPELLANT BURN RATE ORIFICE DIAMETER for BOTH INSIDE and OUTSIDE SURFACE BURNING for 60 ORIFICES

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Enhancement Tool

Perforating Gun Propellant in Lower Portion of Gun

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Summary

(1) PFS Patents: - External Burn with Simulator: 5,295,545

  • Long Burning Propellant: 7,073,589
  • Linear Ignition: 7,409,911B2
  • Restrictor Plug: 7,487,827
  • Closed Vessel Propellant Burn (Patent Pending)
  • Additional Provisional Patent Applications Filed
  • Exclusive with Propellant Supplier (Aerojet);
  • Simulator Developed in Conjunction with Schlumberger;
  • Testing & Fabrication Facility with PV Test Capability;
  • ATF/State Dept. Registration and Approved Facilities Storage;
  • DOT 1.4C for Ease of Shipment