Patents by Inventor Daniel L. Harshman
Daniel L. Harshman has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 5109670Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.Type: GrantFiled: October 15, 1990Date of Patent: May 5, 1992Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 5103633Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.Type: GrantFiled: October 15, 1990Date of Patent: April 14, 1992Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 5097663Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.Type: GrantFiled: October 15, 1990Date of Patent: March 24, 1992Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 5081831Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion. Additionally, the fuel injector is positioned proximate the step and includes a condition responsive mechanism for varying the angle the fuel injector makes with the combustor's longitudinal axis during supersonic flight.Type: GrantFiled: October 15, 1990Date of Patent: January 21, 1992Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 5072582Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.Type: GrantFiled: March 23, 1989Date of Patent: December 17, 1991Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 5072581Abstract: A scramjet combustor for a hypersonic (Mach number greater than about 5.5) flight vehicle. The combustor housing has two spaced-apart, generally opposing, and longitudinally extending walls. Each wall has an aft-facing step. Fuel (such as hydrogen) is injected at the step into the shear zone along the separation line for better fuel-air mixing. The longitudinal distance between the steps is controlled to take advantage of aerothermo compression provided by the forward step's shock. The back portion of each wall is positioned transversely inward toward the combustor's longitudinal axis to improve mixing effectiveness for more efficient combustion.Type: GrantFiled: October 15, 1990Date of Patent: December 17, 1991Assignee: General Electric CompanyInventor: Daniel L. Harshman
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Patent number: 4446696Abstract: A compound propulsor for powering a vehicle, such as an aircraft. A compound propulsor includes a core gas turbine engine, a fan encased within a cowl, at least one propeller, and drive means for distributing a portion of the power produced by the core engine to the fan and another portion to the propeller. Preferably, the compound propulsor also includes variable geometry inlet guide vanes for varying the portions of power distributed to the fan and propeller.Type: GrantFiled: June 29, 1981Date of Patent: May 8, 1984Assignee: General Electric CompanyInventors: Donald F. Sargisson, Daniel L. Harshman