IPC 7 English version F02K !A-F02K 11/00

F02K-F02K01100

SECTION F – MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

F 02

COMBUSTION ENGINES (cyclically operating valves therefor, lubricating, exhausting, or silencing engines F01); HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS

F 02 K

JET-PROPULSION PLANTS (arrangement or mounting of jet-propulsion plants in land vehicles or vehicles in general B60K; arrangement or mounting of jet-propulsion plants in waterborne vessels B63H; controlling aircraft attitude, flight direction, or altitude by jet reaction B64C; arrangement or mounting of jet-propulsion plants in aircraft B64D; plants characterised by the power of the working fluid being divided between jet propulsion and another form of propulsion, e.g. propeller, F02B, F02C; features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C)

Notes

(1)

In this subclass, the following expression is used with the meaning indicated:

–

"jet-propulsion plants" means plants using combustion to produce a fluid stream from which a propulsive thrust on the plants is obtained on the reaction principle.

(2)

Attention is drawn to the Notes preceding class F01.

Subclass Index

PLANTS CHARACTERISED BY JET PIPE OR NOZZLE

F02K 1/00, F02K 9/80

PLANTS WITH COMPRESSOR OR FAN

F02K 3/00, F02K 5/00

PLANTS WITHOUT COMPRESSOR OR FAN

F02K 7/00

ROCKET-ENGINE PLANTS

F02K 9/00

CONTROL

F02K 1/15, F02K 1/76, F02K 7/00, F02K 9/00

OTHER PLANTS

F02K 11/00

Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto (rocket nozzles F02K 9/97)

Mounting of an exhaust cone in the jet pipe

Varying effective area of jet pipe or nozzle (F02K 1/30 takes precedence) [3]

by axially moving or transversely deforming an internal member, e.g. the exhaust cone

by axially moving an external member, e.g. a shroud (F02K 1/12 takes precedence) [3]

by distorting the jet pipe or nozzle

by means of pivoted eyelids [3]

by means of pivoted flaps

Control or regulation [3]

conjointly with another control [3]

with control of fuel supply [3]

automatic [3]

using fluid jets to influence the jet flow [3]

for varying effective area of jet pipe or nozzle [3]

for reversing thrust [3]

for attenuating noise [3]

having an ejector [3]

Introducing air inside the jet (F02K 1/28 takes precedence) [3]

Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet [3]

the means being movable into an inoperative position [3]

Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction (F02K 1/40 takes precedence) [3]

Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing (F02K 1/28, F02K 1/36, F02K 1/38 take precedence) [3]

Corrugated nozzles [3]

Deflecting outwardly a portion of the jet by retractable scoop-like baffles [3]

Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing [3]

Nozzles having means for reversing jet thrust (F02K 1/32 takes precedence) [3]

Reversing jet main flow [3]

Reversers mounted on the inner cone or the nozzle housing [3]

by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers [3]

by blocking the rearward discharge by means of flaps [3]

Reversing fan flow [3]

using reversing fan blades [3]

Reversers mounted on the engine housing downstream of the fan exhaust section [3]

using thrust reverser flaps or doors mounted on the fan housing [3]

the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow [3]

Reversing at least one flow in relation to at least one other flow in a plural-flow engine [3]

Control or regulation of thrust reversers [3]

Other construction of jet pipes [3]

Couplings or connections [3]

Jet pipe walls, e.g. liners [3]

Plants including a gas turbine driving a compressor or a ducted fan

in which part of the working fluid by-passes the turbine and combustion chamber

the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type

with front fan

062

with aft fan [3]

065

with front and aft fans [3]

068

being characterised by a short axial length relative to diameter [3]

072

with counter-rotating rotors [3]

075

controlling flow ratio between flows [3]

077

the plant being of the multiple flow type, i.e. having three or more flows [3]

with supplementary heating of the working fluid (after-burners, combustion chambers F23R); Control thereof (control of fuel supply therefor F02C 9/26) [3]

by after-burners (F02K 3/105 takes precedence) [3]

105

Heating the by-pass flow [3]

by means of burners or combustion chambers [3]

115

by means of indirect heat exchange [3]

characterised by having more than one gas turbine

Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

the engine being of the reciprocating-piston type

Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof (rocket-engine plants F02K 9/00)

the jet being intermittent, i.e. pulse jet

with resonant combustion chambers

with combustion chambers having valves

067

having aerodynamic valves [3]

075

with multiple pulse-jet engines [3]

the jet being continuous

characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Injection-induction jet engines [3]

with external combustion, e.g. scram-jet engines [3]

Composite ram-jet/turbo-jet engines [3]

Composite ram-jet/rocket engines [3]

Composite ram-jet/pulse-jet engines [3]

Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof (chemical composition of propellants C06B, C06D) [3]

using solid propellants (F02K 9/72 takes precedence; using semi-solid or pulverulent propellants F02K 9/70) [3]

Shape or structure of solid propellant charges [3]

made of two or more portions burning at different rates [3]

made from sheet-like materials, e.g. of carpet-roll type, of layered structure [3]

of honeycomb structure [3]

of the internal-burning type having a star or like shaped internal cavity [3]

of the external-burning type [3]

of the front-burning type [3]

Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges [3]

Burning control [3]

having two or more propellant charges with the propulsion gases exhausting through a common nozzle [3]

with the propulsion gases exhausting through a plurality of nozzles [3]

Constructional parts; Details (shape or structure of solid propellant charges F02K 9/10; starting or ignition means or arrangements F02K 9/95; rocket nozzles F02K 9/97) [3]

Casings; Combustion chambers; Liners thereof [3]

Propellant charge supports [3]

Safety devices, e.g. to prevent accidental ignition [3]

Cooling arrangements [3]

using liquid or gaseous propellants (F02K 9/72 takes precedence) [3]

Feeding propellants [3]

using pumps (pumps per se F04) [3]

driven by a gas turbine fed by propellant combustion gases [3]

using pressurised fluid to pressurize the propellants [3]

Injectors (in general B05B) [3]

Leakage detectors; Purging systems; Filtration systems (filters per se B01D) [3]

Control [3]

Propellant feed valves (valves in general F16K) [3]

Constructional parts; Details (starting or ignition means or arrangements F02K 9/95; rocket nozzles F02K 9/97) [3]

Combustion or thrust chambers [3]

having cooling arrangements [3]

of the rotary type [3]

Decomposition chambers [3]

using semi-solid or pulverulent propellants [3]

using liquid and solid propellants, i.e. hybrid rocket-engine plants [3]

combined with another jet-propulsion plant [3]

with another rocket-engine plant; Multistage rocket-engine plants [3]

with an air-breathing jet-propulsion plant (with a ram-jet engine F02K 7/18) [3]

characterised by thrust or thrust vector control (F02K 9/26, F02K 9/56, F02K 9/94 take precedence) [3]

by injection of a secondary fluid into the rocket exhaust gases [3]

using movable nozzles [3]

using nozzle throats of adjustable cross-section [3]

using auxiliary rocket nozzles [3]

using deflectors (F02K 9/82 takes precedence) [3]

incorporating means for reversing or terminating thrust [3]

Re-ignitable or restartable rocket-engine plants; Intermittently operated rocket-engine plants [3]

characterised by starting or ignition means or arrangements (safety devices F02K 9/38) [3]

characterised by specially adapted arrangements for testing or measuring [3]

Rocket nozzles (thrust or thrust vector control F02K 9/80) [3]

11/

Plants not provided for in the preceding groups [3]