GB671427A - Improvements in or relating to gas-turbine engines - Google Patents

Improvements in or relating to gas-turbine engines

Info

Publication number
GB671427A
GB671427A GB2255049A GB2255049A GB671427A GB 671427 A GB671427 A GB 671427A GB 2255049 A GB2255049 A GB 2255049A GB 2255049 A GB2255049 A GB 2255049A GB 671427 A GB671427 A GB 671427A
Authority
GB
United Kingdom
Prior art keywords
grids
grid
air
mouth
guard
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
GB2255049A
Inventor
William Sherlaw
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB2255049A priority Critical patent/GB671427A/en
Publication of GB671427A publication Critical patent/GB671427A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards

Abstract

671,427. Gas turbine plant; centrifugal compressors. ROLLS-ROYCE, Ltd. Aug. 29. 1950 [Aug. 30, 1949], No. 22550/49. Classes 110(i) and 110(iii) A gas turbine engine comprising an air compressor having a circumferentially disposed intake through which air flows radially inwards to the axis of the engine and to which the air flows in a direction parallel to the axis of rotation of the engine, has a guard grid lying in the normal path of the air flow to the engine which has one edge spaced away from the periphery of the mouth of the air intake so as to provide an entrance to behind the guard grid, which entrance faces downstream of the flow of air towards the intake. The gas turbine shown has a compressor 10 with a double sided impeller 10a the vanes 14, 15 of which are supplied with air by passages 17, 18, the mouths of which are provided with guard grids. The guard grid for the passage 17 comprises a main frusto-conical grid part 20 of larger apex angle than that of the mouth. The smaller diameter of the grid 20 is connected with the upstream edge 17a of the mouth and the larger diameter is contained in the plane of, .but spaced radially outwards from the downstream edge 17b of the mouth to form an entrance to behind the grid. A short axially extending grid 23 is attached to the downstream edge 17b. The guard grid for the passage 18 comprises two parts 24, 25. The part 24 is cylindrical and extends from the upstream edge 18a of the mouth of the passage 18 to close to the plane of the downstream edge 18b. The part 25 is contained substantially in the plane of the mouth and extends about one third of the way across it. When the grids are not choked with ice, the air enters the passages 17, 18 through the grids but when these grids are choked the air is forced to flow around the downstream edge of the grids 20, 24 and turn through 180 degrees to the downstream facing entrance. The grids 20, 24 may have the downstream edge formed with a radially outwardly directed tip through which a heating fluid such as oil may by passed. The downstream facing entrances may also be provided with guard grids. Means may be provided to de-ice the grids.
GB2255049A 1949-08-30 1949-08-30 Improvements in or relating to gas-turbine engines Expired GB671427A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2255049A GB671427A (en) 1949-08-30 1949-08-30 Improvements in or relating to gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2255049A GB671427A (en) 1949-08-30 1949-08-30 Improvements in or relating to gas-turbine engines

Publications (1)

Publication Number Publication Date
GB671427A true GB671427A (en) 1952-05-07

Family

ID=10181234

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2255049A Expired GB671427A (en) 1949-08-30 1949-08-30 Improvements in or relating to gas-turbine engines

Country Status (1)

Country Link
GB (1) GB671427A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2760719A (en) * 1952-06-30 1956-08-28 Garrett Corp Compressor
US3187506A (en) * 1963-08-19 1965-06-08 Gen Electric Air induction system
CN112324573A (en) * 2020-10-29 2021-02-05 中国航发湖南动力机械研究所 Aeroengine air inlet cover

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2760719A (en) * 1952-06-30 1956-08-28 Garrett Corp Compressor
US3187506A (en) * 1963-08-19 1965-06-08 Gen Electric Air induction system
CN112324573A (en) * 2020-10-29 2021-02-05 中国航发湖南动力机械研究所 Aeroengine air inlet cover

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