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James L Keirsey

from Frederick, MD
Age ~98
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Related to:
Luanne KeirseyRobert S GoodwinBernice Goodwin, 96Elizabeth DagueCharles Dague, 33Brady Dague, 37David A Dague, 63
Connected to:
Christopher K Keirsey, 60Frank C Keirsey, 68Hanah Keirsey, 29John Keirsey, 60Jennifer Keirstead, 41Marleny L Keiry, 30Daniel G Keis, 55Michael T Keis, 38David A Keisel, 56William H Keisel, 63

James Keirsey Phones & Addresses

  • 8114 Laurel Ridge Rd, Frederick, MD 21702 (301) 694-9586
  • Silver Spring, MD
  • Middletown, MD
  • Sarasota, FL

Work

Position: Food Preparation and Serving Related Occupations

Publications

Us Patents

Variable-Cycle Storable Reactants Engine

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US Patent:
52243443, Jul 6, 1993
Filed:
Sep 4, 1992
Appl. No.:
7/941013
Inventors:
James L. Keirsey - Frederick MD
Don H. Sheppard - Ellicott City MD
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
F02K 928
US Classification:
60244
Abstract:
A variable-cycle storable fuels engine having three cycles is provided. The engine operates as an air-augmented rocket from launch to approximately Mach 3. From approximately Mach 3 to Mach 8, the engine operates as a dual mode ramjet/scramjet to altitudes exceeding 100,000 feet. Thereafter, the engine operates as a conventional pure rocket for final sub-orbital boost. A fixed geometry air inlet provides improved ram recovery at altitudes below 100,000 feet.

Thrust Augmented Rocket

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US Patent:
43278850, May 4, 1982
Filed:
Oct 6, 1971
Appl. No.:
5/187136
Inventors:
Ralph W. Blevins - Columbia MD
James L. Keirsey - Rockville MD
William B. Shippen - Brookeville MD
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
F42B 1516
US Classification:
244 324
Abstract:
Invention is an aerial vehicle that uses a centrally located aft burning id-propellant motor to supply a fuel-rich exhaust to four cylindrical engines which are mounted in equally spaced relation about the exterior of the vehicle body. The fuel-rich exhaust is mixed with air in the engines and burned to provide ramjet action to propel the vehicle. A tandem booster rocket initially propels the vehicle to supersonic speed. Tail fins are interdigitated with respect to the engines and include sections which are movable upon command for steering the vehicle. Among the advantages for the vehicle are its maneuverability and its adaptability to existing missile systems.

Hypersonic Modular Inlet

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US Patent:
41945190, Mar 25, 1980
Filed:
Nov 18, 1964
Appl. No.:
4/412267
Inventors:
Clifford B. Baker - Rockville MD
James L. Keirsey - Rockville MD
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
F02K 1100
US Classification:
137 151
Abstract:
This invention relates to a compact hypersonic modular inlet which divides captured airstream and compresses it supersonically without the need for a variable geometry diffuser. According to the invention, an innerbody is provided with a plurality of perimetrically spaced inlet ducts which are defined by a single concave sidewall. The sidewalls intersect to form a center spike and radially directed, swept back leading edges. A cowling covers the inlets and is provided with a swept back leading edge adjacent to each duct, each leading edge having a profile conforming to a normal shock front.

Multi-Port Dump Combustor

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US Patent:
45398119, Sep 10, 1985
Filed:
Jan 27, 1982
Appl. No.:
6/346986
Inventors:
Lawrence A. Dale - Severna Park MD
Stephen E. Grenleski - Silver Spring MD
James L. Keirsey - Silver Spring MD
Charles E. Stevens - Highland MD
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
F02K 710
US Classification:
602701
Abstract:
A four-ported dump combustor is designed for use with a ramjet engine and ovides high combustion efficiency and pressure recovery for length-to-diameter (L/D) ratios of between 1. 3 and 4. 4, over a range of operating conditions.

Solid Fuel Ramjet Flow Control Device

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US Patent:
46286888, Dec 16, 1986
Filed:
Aug 29, 1983
Appl. No.:
6/527158
Inventors:
James L. Keirsey - Silver Spring MD
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
F02K 710
US Classification:
60251
Abstract:
A device for controlling the rate of fuel generation in a solid fuel ramjet ngine having a translating tube within the fuel grain and air inlet for continuously changing the distribution of air over the fuel grain in response to air mass flow. The distribution of air effects the aerodynamic shear interaction between the air and solid fuel which causes a change in burn rate.
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James L Keirsey from Frederick, MD, age ~98 Get Report