Patent US2220892A successfully refreshed from Google Patents.
Patent US4134260A successfully refreshed from Google Patents.
US4134260A
Expired / Lapsed
US
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Afterburner flow mixing means in turbofan jet engine
Assignee: Rolls Royce Corp
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Filing: 1977-10-25
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Granted: 1979-01-16
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Expires: 1997-10-25
Abstract
Abstract A short length afterburner assembly for a jet propulsion engine having a fan bypass includes cold and hot air cross-over passages and a plurality of flame stabilization swirler vanes associated with a balanced load controller for positioning the vanes parallel to hot gas stream flow from a jet engine core when the afterburner is off and in an inclined position to such gas stream flow when fuel is injected therein during afterburner operation thereby to produce flame spread within the afterburner core by a combination of translatory and swirling motions; and wherein atomized fuel for afterburner combustion is injected into hot gases ducted through hot air cross-over passages from the jet engine core to produce premix and prevaporization of fuel upstream of fixed flameholders and wherein cold fan bypass air cross-over passages have movable turbulator grids positioned during afterburner operation for mixing cold air flow with the bypassed hot core gas at the fixed flameholders during afterburner operation and wherein the turbulator grids are positioned parallel to gas flow when the afterburner is not in operation by means of the balanced load controller to produce a balanced variable geometry mechanical load to that on the flame stabilization swirler vanes.
Inventors
- 👤 Arthur H. Lefebvre
- 👤 Samuel B. Reider
- 👤 Jerry G. Tomlinson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 15:00
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/16; F23R3/18; F23R3/22
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
254 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for creating turbulence and mixing cold air flow with the flame front at the cold air duct outlet, operator means connected to said turbulator vanes and operative to position said vanes against one another in a straight line position to prevent flow disturbance during normal operation and operative to position said turbulator vanes in a spread-wing position to produce maximized flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core gas exhaust duct and connected to said operator means to be positioned to produce a combination translatory and swirl motion flow from said core heat exhaust duct, said swirler vanes being positioned against one another by said operator means in a straight line axial position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
Claim 2
Dependent Claim
254 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for creating turbulence and mixing cold air flow with the flame front at the cold air duct outlet, operator means connected to said turbulator vanes and operative to position said vanes against one another in a straight line position to prevent flow disturbance during normal operation and operative to position said turbulator vanes in a spread-wing position to produce maximized flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core gas exhaust duct and connected to said operator means to be positioned to produce a combination translatory and swirl motion flow from said core heat exhaust duct, said swirler vanes being positioned against one another by said operator means in a straight line axial position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
Claim 3
Dependent Claim
280 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for promoting turbulence and mixing cold air flow with the flame front at the cold air duct outlet, first and second rotatably adjustable, telescoped shafts connected to said turbulator vanes and operative to position said vanes against one another in an engine straight line position to prevent flow distrubance during normal operation and operative to position said turbulator vanes in a spread-wing position to maximize the flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core heat gas exhaust duct to produce a combination translatory and swirl motion in outlet flow from said core heat exhaust duct, said swirler vanes being connected to said telescoped shafts, means including said telescoped shafts for locating said plurality of swirler vanes to produce the combination translatory and swirl motion and to position said swirler vanes against one another in an axial straight line position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
Claim 4
Dependent Claim
280 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for promoting turbulence and mixing cold air flow with the flame front at the cold air duct outlet, first and second rotatably adjustable, telescoped shafts connected to said turbulator vanes and operative to position said vanes against one another in an engine straight line position to prevent flow distrubance during normal operation and operative to position said turbulator vanes in a spread-wing position to maximize the flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core heat gas exhaust duct to produce a combination translatory and swirl motion in outlet flow from said core heat exhaust duct, said swirler vanes being connected to said telescoped shafts, means including said telescoped shafts for locating said plurality of swirler vanes to produce the combination translatory and swirl motion and to position said swirler vanes against one another in an axial straight line position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
Claim 5
Dependent Claim
289 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for promoting turbulence and mixing cold air flow with the flame front at the cold air duct outlet, first and second rotatably adjustable, first and second telescoped shafts connected to said turbulator vanes and operative to position said vanes against one another in an axial straight line position to prevent flow disturbance during normal operation and operative to position said turbulator vanes in a spread-wing position to produce maximized flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core heat gas exhaust duct to produce a combination translatory and swirl motion in outlet flow from said core heat exhaust duct, said swirler vanes being connected respectively to said first and second shafts to assume a spread-wing position and to produce a torque thereon to counterbalance aerodynamic forces on said turbulator vanes when in their spread-wing position, said swirler vanes being positioned against one another in an axial straight line position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
Claim 6
Dependent Claim
289 words
An afterburner assembly for a turbofan jet engine with a fan bypass and a core engine comprising an outer annular cold air duct having an inlet connected to the bypass fan discharge and an outlet, an internal core heat exhaust duct having an inlet in communication with the turbojet exhaust and an outlet, chute means forming a plurality of crossover passages communicating the core heat exhaust duct with the cold air duct outlet, means for directing fuel spray into said crossover passages to be vaporized by hot exhaust gas therein, a flameholder in the outlet of each chute means to maintain a flame front at the cold air duct outlet, a pair of perforated turbulator vanes in said outlet for promoting turbulence and mixing cold air flow with the flame front at the cold air duct outlet, first and second rotatably adjustable, first and second telescoped shafts connected to said turbulator vanes and operative to position said vanes against one another in an axial straight line position to prevent flow disturbance during normal operation and operative to position said turbulator vanes in a spread-wing position to produce maximized flow turbulence during afterburner operation, and a plurality of swirler vanes located within said internal core heat gas exhaust duct to produce a combination translatory and swirl motion in outlet flow from said core heat exhaust duct, said swirler vanes being connected respectively to said first and second shafts to assume a spread-wing position and to produce a torque thereon to counterbalance aerodynamic forces on said turbulator vanes when in their spread-wing position, said swirler vanes being positioned against one another in an axial straight line position to permit smooth exhaust flow from said exhaust duct during normal jet engine operation.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-01-15 | 1982-07-17 | 1983-01-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-01-15 | 1986-07-17 | 1987-01-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-01-15 | 1990-07-17 | 1991-01-16 | $7700.00 | Window Closed / Lapsed |