GB471371A - Cooling of aircraft engines - Google Patents
Cooling of aircraft enginesInfo
- Publication number
- GB471371A GB471371A GB673136A GB673136A GB471371A GB 471371 A GB471371 A GB 471371A GB 673136 A GB673136 A GB 673136A GB 673136 A GB673136 A GB 673136A GB 471371 A GB471371 A GB 471371A
- Authority
- GB
- United Kingdom
- Prior art keywords
- exit
- engine
- air
- flap
- hinged
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P7/00—Controlling of coolant flow
- F01P7/02—Controlling of coolant flow the coolant being cooling-air
- F01P7/023—Cowlings for airplane engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
471,371. Cooling means for aero engines. ELLOR, J. E., and PARAVICINI, T. P. DE. March 5, 1936,No.6731. [Class 4] Means for controlling the flow of air through a duct in which are placed cooling surfaces of an aero engine comprise one or more adjustable flaps or shutters hinged at the rear edge and adapted when moved about their hinges more or less to obstruct the air exit from the duct, each flap or shutter pointing forward into the airstream leaving the duct. As applied to a radiator duct, Fig. 1, a flap C<1> of aerofoil section is hinged to the fuselage at C at the rear boundary of the exit and is controlled manually or automatically, e.g. by a thermostat between extreme positions, in one of which the flap is nested in recess C<3> and in the other the flap completely closes the exit. As applied to an air-cooled engine with a ring cowling, Fig. 2, flaps D<3> of aerofoil section are hinged to the fuselage at D<4>. In an application to an aircooled engine with a cowling E<2> having a forward annular air exit at F, the area of the exit is controlled by flaps G<1> of streamline section hinged to the cowling at G. In this form the engine cooling air is taken through slots E<4> at the leading edge of a wing E3 on which the engine is mounted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB673136A GB471371A (en) | 1936-03-05 | 1936-03-05 | Cooling of aircraft engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB673136A GB471371A (en) | 1936-03-05 | 1936-03-05 | Cooling of aircraft engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB471371A true GB471371A (en) | 1937-09-03 |
Family
ID=9819737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB673136A Expired GB471371A (en) | 1936-03-05 | 1936-03-05 | Cooling of aircraft engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB471371A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5135999A (en) * | 1974-09-20 | 1976-03-26 | Fuji Heavy Ind Ltd | KOKUENJINREIKYAKUKUKICHOSETSUSOCHI |
| US20160245161A1 (en) * | 2015-02-20 | 2016-08-25 | Pratt & Whitney Canada Corp. | Compound engine assembly with modulated flow |
| US9797297B2 (en) | 2015-02-20 | 2017-10-24 | Pratt & Whitney Canada Corp. | Compound engine assembly with common inlet |
| US9879591B2 (en) | 2015-02-20 | 2018-01-30 | Pratt & Whitney Canada Corp. | Engine intake assembly with selector valve |
| US9932892B2 (en) | 2015-02-20 | 2018-04-03 | Pratt & Whitney Canada Corp. | Compound engine assembly with coaxial compressor and offset turbine section |
-
1936
- 1936-03-05 GB GB673136A patent/GB471371A/en not_active Expired
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5135999A (en) * | 1974-09-20 | 1976-03-26 | Fuji Heavy Ind Ltd | KOKUENJINREIKYAKUKUKICHOSETSUSOCHI |
| US20160245161A1 (en) * | 2015-02-20 | 2016-08-25 | Pratt & Whitney Canada Corp. | Compound engine assembly with modulated flow |
| US9797297B2 (en) | 2015-02-20 | 2017-10-24 | Pratt & Whitney Canada Corp. | Compound engine assembly with common inlet |
| US9879591B2 (en) | 2015-02-20 | 2018-01-30 | Pratt & Whitney Canada Corp. | Engine intake assembly with selector valve |
| US9896998B2 (en) * | 2015-02-20 | 2018-02-20 | Pratt & Whitney Canada Corp. | Compound engine assembly with modulated flow |
| US9932892B2 (en) | 2015-02-20 | 2018-04-03 | Pratt & Whitney Canada Corp. | Compound engine assembly with coaxial compressor and offset turbine section |
| US10533487B2 (en) | 2015-02-20 | 2020-01-14 | Pratt & Whitney Canada Corp. | Engine intake assembly with selector valve |
| US10533489B2 (en) | 2015-02-20 | 2020-01-14 | Pratt & Whitney Canada Corp. | Compound engine assembly with common inlet |
| US10883414B2 (en) | 2015-02-20 | 2021-01-05 | Pratt & Whitney Canada Corp. | Engine intake assembly with selector valve |
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