GB623142A - Improvements in or relating to the air intakes of an internal combustion power plant - Google Patents
Improvements in or relating to the air intakes of an internal combustion power plantInfo
- Publication number
- GB623142A GB623142A GB10546/47A GB1054647A GB623142A GB 623142 A GB623142 A GB 623142A GB 10546/47 A GB10546/47 A GB 10546/47A GB 1054647 A GB1054647 A GB 1054647A GB 623142 A GB623142 A GB 623142A
- Authority
- GB
- United Kingdom
- Prior art keywords
- opening
- passage
- shutters
- shutter
- intake
- 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
- 238000002485 combustion reaction Methods 0.000 title 1
- 239000007789 gas Substances 0.000 abstract 6
- 230000004048 modification Effects 0.000 abstract 3
- 238000012986 modification Methods 0.000 abstract 3
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
623,142. Air inlets for gas turbines. NAPIER & SON, Ltd., D., SAMMONS, H., and COWDREY, C. L. April 21, 1947, Nos. 10546 and 23707. [Class 4] [Also in Group XXVI] An air intake system for a gas turbine plant subject to icing conditions comprises in combination an annular intake passage F, Fig. 1, running in the fore-and-aft direction, an annular forwardly facing intake opening which is opened or closed by shutter members M rotatable about radial axes, an annular opening K in the outer wall of the intake passage through which air can enter the passage laterally when the forwardly facing intake is closed and means P<SP>1</SP> for supplying hot gases to the forwardly facing intake from which they flow through the shutter members. The annular opening K may be provided with a sliding shutter L which closes the opening when the forwardly facing intake is open. The shutter L may be connected through levers M<SP>3</SP>, Fig. 9, with some of the operating levers M<SP>2</SP> of the shutters M so that when the shutters are closed the annular opening K is open and vice versa. The levers M<SP>2</SP> may be operated by motor O<SP>3</SP> acting through a worm O<SP>1</SP>, a toothed sector O and a link N. The air entering the opening K is taken from the boundary layer of the nacelle through an opening H<SP>2</SP> and is heated by passing over the engine. The hot gases are taken from the exhaust pipe of the engine through the pipe P<SP>1</SP> to the hollow fairing G from where they pass through the hollow bearing pins M<SP>1</SP> into the hollow shutters M. The gases leaving the shutter may be used to heat the nose-piece J. In a modification, Fig. 4, the annular opening is connected directly with the boundary layer adjacent the nosepiece J by a passage K<SP>1</SP> provided with gill-like flaps L<SP>2</SP> adapted to open and close the passage as the shutters M are rotated. In a modification of this arrangement, the passage K<SP>1</SP> is open or closed by a ring-like shutter. In a further modification, the hot gases are supplied to the nose-piece J and pass radially inwards to the shutters M. Specification 592,091 is referred to. Reference has been directed by the Comptroller to Specification 619,390.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10546/47A GB623142A (en) | 1947-04-21 | 1947-04-21 | Improvements in or relating to the air intakes of an internal combustion power plant |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10546/47A GB623142A (en) | 1947-04-21 | 1947-04-21 | Improvements in or relating to the air intakes of an internal combustion power plant |
Publications (1)
Publication Number | Publication Date |
---|---|
GB623142A true GB623142A (en) | 1949-05-12 |
Family
ID=9969821
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB10546/47A Expired GB623142A (en) | 1947-04-21 | 1947-04-21 | Improvements in or relating to the air intakes of an internal combustion power plant |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB623142A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3548597A (en) * | 1968-09-16 | 1970-12-22 | Alexander Hossen Etessam | Turbine engine for aircraft having a supplementary compressor driven by a supplementary turbine |
GB2224779A (en) * | 1988-10-03 | 1990-05-16 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
US9938848B2 (en) | 2015-04-23 | 2018-04-10 | Pratt & Whitney Canada Corp. | Rotor assembly with wear member |
US9957807B2 (en) | 2015-04-23 | 2018-05-01 | Pratt & Whitney Canada Corp. | Rotor assembly with scoop |
US10145301B2 (en) | 2014-09-23 | 2018-12-04 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US10378554B2 (en) | 2014-09-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US10690146B2 (en) | 2017-01-05 | 2020-06-23 | Pratt & Whitney Canada Corp. | Turbofan nacelle assembly with flow disruptor |
US10724540B2 (en) | 2016-12-06 | 2020-07-28 | Pratt & Whitney Canada Corp. | Stator for a gas turbine engine fan |
-
1947
- 1947-04-21 GB GB10546/47A patent/GB623142A/en not_active Expired
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3548597A (en) * | 1968-09-16 | 1970-12-22 | Alexander Hossen Etessam | Turbine engine for aircraft having a supplementary compressor driven by a supplementary turbine |
GB2224779A (en) * | 1988-10-03 | 1990-05-16 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
GB2224779B (en) * | 1988-10-03 | 1993-03-31 | Gen Electric | Aircraft engine inlet cowl anti-icing system |
US10145301B2 (en) | 2014-09-23 | 2018-12-04 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US10378554B2 (en) | 2014-09-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US10837361B2 (en) | 2014-09-23 | 2020-11-17 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US11118601B2 (en) | 2014-09-23 | 2021-09-14 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US9938848B2 (en) | 2015-04-23 | 2018-04-10 | Pratt & Whitney Canada Corp. | Rotor assembly with wear member |
US9957807B2 (en) | 2015-04-23 | 2018-05-01 | Pratt & Whitney Canada Corp. | Rotor assembly with scoop |
US10724540B2 (en) | 2016-12-06 | 2020-07-28 | Pratt & Whitney Canada Corp. | Stator for a gas turbine engine fan |
US10690146B2 (en) | 2017-01-05 | 2020-06-23 | Pratt & Whitney Canada Corp. | Turbofan nacelle assembly with flow disruptor |
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