GB1258315A - - Google Patents

Info

Publication number
GB1258315A
GB1258315A GB1258315DA GB1258315A GB 1258315 A GB1258315 A GB 1258315A GB 1258315D A GB1258315D A GB 1258315DA GB 1258315 A GB1258315 A GB 1258315A
Authority
GB
United Kingdom
Prior art keywords
bores
nozzles
support ring
engine
fluid
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
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 filed Critical
Publication of GB1258315A publication Critical patent/GB1258315A/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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/212—Heat transfer, e.g. cooling by water injection

Abstract

1,258,315. Gas turbine engines; air intakes. GENERAL ELECTRIC CO. Feb. 25, 1969 [March 4, 1968], No.9942/69. Heading F1G. The invention relates to a spray apparatus which is adapted to be removably secured to a gas turbine engine to permit fluid to be sprayed radially inwardly of and axially along the air intake stream of the engine, the apparatus comprising a support ring on which a plurality of spray nozzles are mounted. In the embodiment shown, the support ring 26 is formed with a bore 27 so that when the ring is secured to the engine 10 by a ring clamp 86, the bore 27 is aligned with the intake duct. Four spray nozzle assemblies 30, 32, 34, 36 are mounted on the support ring, each assembly comprising a pair of nozzles 38, 40 which are mounted in a nozzle block 42 formed with bores 44, 46. Each nozzle block is secured to a connector block 56 which is formed with bores 66, 68, 70, 72 and is secured to the support ring. Two conduits 58, 60 extend from an inlet connection 54 having two inlets 62, 44, the conduit 58 connecting through bores 66, 70, 44 with the spray nozzles 38 through which one fluid such as cleaning or thrust augmentation fluid may be supplied to the engine intake air, and the conduit 60 connecting through bores 68, 72, 46 with the spray nozzles 40 through which another fluid such as preservative fluid may be supplied to the engine intake air. The support ring 26 is recessed at 52 in the region of the spray nozzles so that the nozzles do not project into the air stream. The nozzles are provided with enlargements 55 to prevent them passing through the bores 48 and into the engine intake.
GB1258315D 1968-03-04 1969-02-25 Expired GB1258315A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US71017168A 1968-03-04 1968-03-04

Publications (1)

Publication Number Publication Date
GB1258315A true GB1258315A (en) 1971-12-30

Family

ID=24852911

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1258315D Expired GB1258315A (en) 1968-03-04 1969-02-25

Country Status (4)

Country Link
BE (1) BE729268A (en)
DE (1) DE1910557A1 (en)
FR (1) FR2003200A1 (en)
GB (1) GB1258315A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2540521C2 (en) * 2012-07-02 2015-02-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Самарский государственный аэрокосмический университет имени академика С.П. Королева (национальный исследовательский университет)" (СГАУ) Method of determination of rational parameters of modes of wet cleaning of gte flow duct

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4083181A (en) * 1976-06-14 1978-04-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Gas turbine engine with recirculating bleed
DE3526343A1 (en) * 1985-07-23 1987-02-05 Proizv Ob Turbomotornyj Z Im K Axial flow gas turbine
DE8712157U1 (en) * 1987-09-08 1987-10-29 Techno-Polymer Hans-J. Kuhl, 5982 Neuenrade, De
FR2652365B1 (en) * 1989-09-28 1992-01-10 Masair ANTI-GLARE SCREEN.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2540521C2 (en) * 2012-07-02 2015-02-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Самарский государственный аэрокосмический университет имени академика С.П. Королева (национальный исследовательский университет)" (СГАУ) Method of determination of rational parameters of modes of wet cleaning of gte flow duct

Also Published As

Publication number Publication date
DE1910557A1 (en) 1969-09-25
FR2003200A1 (en) 1969-11-07
BE729268A (en) 1969-08-18

Similar Documents

Publication Publication Date Title
US3623668A (en) Wash manifold
GB1441763A (en) Fuel distribution and injection systems for augmented gas turbine engines
GB1069033A (en) Improvements in or relating to gas turbine jet propulsion engines
ES421165A1 (en) Turbine housing
GB852829A (en) Improvements in or relating to gas-turbine jet propulsion engines
GB745630A (en) Fluid flow control device for jet propulsion nozzles
GB938553A (en) Reheat combustion apparatus for a gas turbine engine
GB1258315A (en)
US3085396A (en) Gas turbine engine with gas starter
GB904142A (en) Improvements in or relating to gas-turbine engines
GB1194716A (en) Improved Base-Thrust Nozzles for Jet Propulsion Engines
GB591113A (en) Improvements relating to the construction and mounting of fuel burner nozzles, especially for gas turbines and like apparatus
GB822299A (en) Improvements in or relating to devices for steering jet propelled aircraft
GB1013116A (en) Improvements in aircraft propulsion power units
GB851153A (en) Gas turbine jet-propulsion engine of the by-pass type
GB974722A (en) Gas turbine jet propulsion engine
GB723110A (en) Improvements in or relating to gas-turbine engines
GB1134996A (en) Jet noise suppressor in jet engine
GB701320A (en) Improvements in or relating to combustion equipment of gas-turbine engines
GB913312A (en) Jet propulsion engine
GB888080A (en) Improvements in or relating to gas turbine engines
GB733727A (en) Improvements in arrangements for deflecting fluid jets
GB919113A (en) Improvements in or relating to aircraft propulsive means
SE197021C1 (en)
GB898525A (en) Improvements in and relating to means for varying the direction of flow of a fluid stream

Legal Events

Date Code Title Description
PS Patent sealed
746 Register noted 'licences of right' (sect. 46/1977)
PE20 Patent expired after termination of 20 years