GB1070458A - Separator for removing foreign matter from a gas stream - Google Patents
Separator for removing foreign matter from a gas streamInfo
- Publication number
- GB1070458A GB1070458A GB24019/65A GB2401965A GB1070458A GB 1070458 A GB1070458 A GB 1070458A GB 24019/65 A GB24019/65 A GB 24019/65A GB 2401965 A GB2401965 A GB 2401965A GB 1070458 A GB1070458 A GB 1070458A
- Authority
- GB
- United Kingdom
- Prior art keywords
- inlet
- duct
- assembly
- particles
- air
- 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
- 239000007789 gas Substances 0.000 abstract 4
- 239000002245 particle Substances 0.000 abstract 4
- 238000007599 discharging Methods 0.000 abstract 1
- 239000011152 fibreglass Substances 0.000 abstract 1
- 239000007788 liquid Substances 0.000 abstract 1
- 238000000926 separation method Methods 0.000 abstract 1
- 239000007787 solid Substances 0.000 abstract 1
- 239000007858 starting material Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/02—Air cleaners
- F02M35/08—Air cleaners with means for removing dust, particles or liquids from cleaners; with means for indicating clogging; with by-pass means; Regeneration of cleaners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B04—CENTRIFUGAL APPARATUS OR MACHINES FOR CARRYING-OUT PHYSICAL OR CHEMICAL PROCESSES
- B04C—APPARATUS USING FREE VORTEX FLOW, e.g. CYCLONES
- B04C3/00—Apparatus in which the axial direction of the vortex flow following a screw-thread type line remains unchanged ; Devices in which one of the two discharge ducts returns centrally through the vortex chamber, a reverse-flow vortex being prevented by bulkheads in the central discharge duct
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cyclones (AREA)
Abstract
1,070,458. Separating particles from gases. BOEING CO. June 4, 1965 [June 12, 1964], No. 24019/65. Addition to 1,065,561. Heading BIT. [Also in Division F1] An air inlet assembly 14, used in conjunction with a gas turbine or other air consuming plant 10, comprises an air inlet 16, a generally annular passage 20 leading to plant 10 and a secondary opening 17, which receives 5% of incoming air and most of the entrained solid and liquid particles and which directs them through a secondary duct 22 at an angle of 45 degrees to the inlet axis. Duct 22 may communicate with an exhaust fan, discharging to the open, but in the embodiment shown a swirl separator 25 having radial vanes 26 effects centrifugal separation of the entrained particles while the remaining gas is returned by duct 24 to the main stream. When the assembly is used with a gas turbine the casing 15 may contain the starter motor thereof. The assembly is made of fibre glass, and is aerodynamically shaped to ensure streamline flow throughout. The inlet 16 may be of equal or greater cross-sectional area than secondary inlet 17. A flat plate 19, at the inlet end, directs heavy particles such as birds into the inlet 17. The passage 20 is of inverted U section at its inlet end but becomes annular downstream of the point where it is joined by duct 24. Instead of the circular configuration illustrated the assembly could have a generally rectangular cross-sectional form. An upstanding vortex generator 28 may be supplied to eliminate the "surge".
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US37460564A | 1964-06-12 | 1964-06-12 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1070458A true GB1070458A (en) | 1967-06-01 |
Family
ID=23477529
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB24019/65A Expired GB1070458A (en) | 1964-06-12 | 1965-06-04 | Separator for removing foreign matter from a gas stream |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR1440966A (en) |
| GB (1) | GB1070458A (en) |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2131882A (en) * | 1982-11-26 | 1984-06-27 | Gen Electric | Gas turbine engine air inlet particle separator |
| FR2538452A1 (en) * | 1982-12-27 | 1984-06-29 | Gen Electric | INLET AIR FLOW PARTICLE SEPARATOR FOR GAS TURBINE ENGINE |
| EP1546526A2 (en) * | 2002-08-12 | 2005-06-29 | Rolls-Royce Corporation | Particle separator for a turbine engine |
| EP2071155A2 (en) * | 2007-12-14 | 2009-06-17 | United Technologies Corporation | Nacelle assembly with turbulators |
| US8192147B2 (en) | 2007-12-14 | 2012-06-05 | United Technologies Corporation | Nacelle assembly having inlet bleed |
| US8209953B2 (en) | 2006-11-10 | 2012-07-03 | United Technologies Corporation | Gas turbine engine system providing simulated boundary layer thickness increase |
| US8282037B2 (en) | 2007-11-13 | 2012-10-09 | United Technologies Corporation | Nacelle flow assembly |
| US8353164B2 (en) | 2006-10-20 | 2013-01-15 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
| US8402739B2 (en) | 2007-06-28 | 2013-03-26 | United Technologies Corporation | Variable shape inlet section for a nacelle assembly of a gas turbine engine |
| US8727267B2 (en) | 2007-05-18 | 2014-05-20 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
| US9228534B2 (en) | 2007-07-02 | 2016-01-05 | United Technologies Corporation | Variable contour nacelle assembly for a gas turbine engine |
| WO2016032585A3 (en) * | 2014-05-29 | 2016-04-28 | General Electric Company | Turbine engine, components, and methods of cooling same |
| US9915176B2 (en) | 2014-05-29 | 2018-03-13 | General Electric Company | Shroud assembly for turbine engine |
| US9988936B2 (en) | 2015-10-15 | 2018-06-05 | General Electric Company | Shroud assembly for a gas turbine engine |
| US10036319B2 (en) | 2014-10-31 | 2018-07-31 | General Electric Company | Separator assembly for a gas turbine engine |
| US10167725B2 (en) | 2014-10-31 | 2019-01-01 | General Electric Company | Engine component for a turbine engine |
| US10286407B2 (en) | 2007-11-29 | 2019-05-14 | General Electric Company | Inertial separator |
| US10428664B2 (en) | 2015-10-15 | 2019-10-01 | General Electric Company | Nozzle for a gas turbine engine |
| US10704425B2 (en) | 2016-07-14 | 2020-07-07 | General Electric Company | Assembly for a gas turbine engine |
| US11033845B2 (en) | 2014-05-29 | 2021-06-15 | General Electric Company | Turbine engine and particle separators therefore |
| US11918943B2 (en) | 2014-05-29 | 2024-03-05 | General Electric Company | Inducer assembly for a turbine engine |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4265646A (en) * | 1979-10-01 | 1981-05-05 | General Electric Company | Foreign particle separator system |
| GB2069054B (en) * | 1980-02-09 | 1983-06-02 | Rolls Royce | Water separator gas turbine engine intake |
-
1965
- 1965-06-04 GB GB24019/65A patent/GB1070458A/en not_active Expired
- 1965-06-08 FR FR19918A patent/FR1440966A/en not_active Expired
Cited By (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4527387A (en) * | 1982-11-26 | 1985-07-09 | General Electric Company | Particle separator scroll vanes |
| GB2131882A (en) * | 1982-11-26 | 1984-06-27 | Gen Electric | Gas turbine engine air inlet particle separator |
| GB2177162A (en) * | 1982-12-27 | 1987-01-14 | Gen Electric | Inlet particle separator for gas turbine engine |
| US4685942A (en) * | 1982-12-27 | 1987-08-11 | General Electric Company | Axial flow inlet particle separator |
| FR2538452A1 (en) * | 1982-12-27 | 1984-06-29 | Gen Electric | INLET AIR FLOW PARTICLE SEPARATOR FOR GAS TURBINE ENGINE |
| GB2133475A (en) * | 1982-12-27 | 1984-07-25 | Gen Electric | Gas turbine engine inlet particle seperator |
| EP1546526A2 (en) * | 2002-08-12 | 2005-06-29 | Rolls-Royce Corporation | Particle separator for a turbine engine |
| EP1546526A4 (en) * | 2002-08-12 | 2005-11-02 | Rolls Royce Corp | Particle separator for a turbine engine |
| US8353164B2 (en) | 2006-10-20 | 2013-01-15 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
| US8844294B2 (en) | 2006-10-20 | 2014-09-30 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
| US8726632B2 (en) | 2006-10-20 | 2014-05-20 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
| US8209953B2 (en) | 2006-11-10 | 2012-07-03 | United Technologies Corporation | Gas turbine engine system providing simulated boundary layer thickness increase |
| US8727267B2 (en) | 2007-05-18 | 2014-05-20 | United Technologies Corporation | Variable contraction ratio nacelle assembly for a gas turbine engine |
| US8402739B2 (en) | 2007-06-28 | 2013-03-26 | United Technologies Corporation | Variable shape inlet section for a nacelle assembly of a gas turbine engine |
| US9228534B2 (en) | 2007-07-02 | 2016-01-05 | United Technologies Corporation | Variable contour nacelle assembly for a gas turbine engine |
| US8282037B2 (en) | 2007-11-13 | 2012-10-09 | United Technologies Corporation | Nacelle flow assembly |
| US9004399B2 (en) | 2007-11-13 | 2015-04-14 | United Technologies Corporation | Nacelle flow assembly |
| US8596573B2 (en) | 2007-11-13 | 2013-12-03 | United Technologies Corporation | Nacelle flow assembly |
| US10286407B2 (en) | 2007-11-29 | 2019-05-14 | General Electric Company | Inertial separator |
| EP2071155A2 (en) * | 2007-12-14 | 2009-06-17 | United Technologies Corporation | Nacelle assembly with turbulators |
| US8186942B2 (en) | 2007-12-14 | 2012-05-29 | United Technologies Corporation | Nacelle assembly with turbulators |
| US8192147B2 (en) | 2007-12-14 | 2012-06-05 | United Technologies Corporation | Nacelle assembly having inlet bleed |
| EP2071155A3 (en) * | 2007-12-14 | 2012-02-22 | United Technologies Corporation | Nacelle assembly with turbulators |
| US10975731B2 (en) | 2014-05-29 | 2021-04-13 | General Electric Company | Turbine engine, components, and methods of cooling same |
| WO2016032585A3 (en) * | 2014-05-29 | 2016-04-28 | General Electric Company | Turbine engine, components, and methods of cooling same |
| US9915176B2 (en) | 2014-05-29 | 2018-03-13 | General Electric Company | Shroud assembly for turbine engine |
| US11918943B2 (en) | 2014-05-29 | 2024-03-05 | General Electric Company | Inducer assembly for a turbine engine |
| US11541340B2 (en) | 2014-05-29 | 2023-01-03 | General Electric Company | Inducer assembly for a turbine engine |
| US11033845B2 (en) | 2014-05-29 | 2021-06-15 | General Electric Company | Turbine engine and particle separators therefore |
| US10167725B2 (en) | 2014-10-31 | 2019-01-01 | General Electric Company | Engine component for a turbine engine |
| US10036319B2 (en) | 2014-10-31 | 2018-07-31 | General Electric Company | Separator assembly for a gas turbine engine |
| US10428664B2 (en) | 2015-10-15 | 2019-10-01 | General Electric Company | Nozzle for a gas turbine engine |
| US9988936B2 (en) | 2015-10-15 | 2018-06-05 | General Electric Company | Shroud assembly for a gas turbine engine |
| US10704425B2 (en) | 2016-07-14 | 2020-07-07 | General Electric Company | Assembly for a gas turbine engine |
| US11199111B2 (en) | 2016-07-14 | 2021-12-14 | General Electric Company | Assembly for particle removal |
Also Published As
| Publication number | Publication date |
|---|---|
| FR1440966A (en) | 1966-06-03 |
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