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 plant

Info

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
Application number
GB10546/47A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB10546/47A priority Critical patent/GB623142A/en
Publication of GB623142A publication Critical patent/GB623142A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02De-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.
GB10546/47A 1947-04-21 1947-04-21 Improvements in or relating to the air intakes of an internal combustion power plant Expired GB623142A (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (11)

* Cited by examiner, † Cited by third party
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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