WO2018138730A1 - Performance enhancing aspirator apparatus - Google Patents
Performance enhancing aspirator apparatus Download PDFInfo
- Publication number
- WO2018138730A1 WO2018138730A1 PCT/IN2017/000091 IN2017000091W WO2018138730A1 WO 2018138730 A1 WO2018138730 A1 WO 2018138730A1 IN 2017000091 W IN2017000091 W IN 2017000091W WO 2018138730 A1 WO2018138730 A1 WO 2018138730A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- performance enhancing
- aspirator apparatus
- aspirator
- shaped casing
- Prior art date
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
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/51—Inlet
- F05D2250/511—Inlet augmenting, i.e. with intercepting fluid flow cross sectional area greater than the rest of the machine behind the inlet
-
- 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
- F05D2260/60—Fluid transfer
- F05D2260/601—Fluid transfer using an ejector or a jet pump
Definitions
- the invention disclosed herein generally relates to gas turbines. More particularly, the invention relates to a performance enhancing aspirator apparatus for improving efficiency of a gas turbine by drawing in surplus air.
- Gas turbines are a type of internal combustion engine. Typically, they have a compressor coupled to a turbine separated by a combustion chamber. The gas turbine operates similar to a steam power plant, with the water replaced by air as the working fluid. The compressor exerts a high pressure on the incoming atmospheric air. Fuel is then sprayed into the combustion chamber, which receives the compressed air, to ignite and release energy. This high-pressure gas enters the turbine, where it expands to a low pressure producing work output by rotating the turbine shaft. However, a large proportion of the energy generated is lost as exhaust gases. An apparatus, which enhances the performance of a gas turbine, is required. Furthermore, an apparatus, which reduces the operational cost and fuel intake of a gas turbine, is required. [0003] Hence, there is a long felt but unresolved need for an apparatus, which enhances the performance of a gas turbine. Furthermore, there is a need for an apparatus, which reduces the operational cost and fuel intake of a gas turbine.
- the performance enhancing aspirator apparatus disclosed herein addresses the above-mentioned need for an apparatus* which enhances the performance of a gas turbine. Furthermore, the invention addresses a need for an apparatus, which reduces the operational cost and fuel intake of a gas turbine.
- the performance enhancing aspirator apparatus for improving efficiency of a gas turbine by drawing in surplus air comprises attachment members and a substantially funnel shaped casing.
- the attachment members are positioned radially on an exterior surface of the gas turbine.
- the substantially funnel shaped casing is fixedly attached to the exteri or surface of the gas turbine via the attachment members.
- the substantially funnel shaped casing and the gas turbine define a converging duct therebetween.
- the converging duct creates a very low-pressure region proximal to a nozzle of the gas turbine, thereby drawing in surplus air for improving efficiency of the gas turbine.
- FIG. 1 exemplarily illustrates a right side elevation view of a performance enhancing aspirator apparatus.
- FIG. 2 exemplarily i llustrates a front elevation view of a performance enhancing aspirator apparatus.
- FIG. 1 exemplarily illustrates a right side elevation view of a performance enhancing aspirator apparatus 100.
- the performance enhancing aspirator apparatus 100 for improving efficiency of a gas turbine 101 by drawing in surplus air comprises attachment members 102 and a substantially funnel shaped casing 103.
- the attachment members 102 are positioned radially on an exterior surface 101a of the gas turbine 101.
- the substantially funnel shaped casing 103 is fixedly attached to the exterior surface 101a of the gas turbine 101 via the attachment members 102.
- the substantially funnel shaped casing 103 and the gas turbine 101 defining a converging duct 104 therebetween.
- the converging duct .104 creates a very low-pressure region proximal to a nozzle 105 of the gas turbine 101, thereby drawing in surplus air for improving efficiency of the gas turbine 101.
- the performance enhancing aspirator apparatus 100 aims to increase the gas turbine 101 efficiency by using the substantially funnel shaped casing 103, without using any extra fuel.
- the exhaust coming out of the nozzle 105 of the gas turbine 101 is further passed through the performance enhancing aspirator apparatus 100, which draws in surplus air, other than the air sucked in by the fan.
- performance enhancing aspirator apparatus 100 comprises a plurality of guide vanes for directing air to the converging duct 104.
- the performance enhancing aspirator apparatus 100 is installed on a gas turbine 101, for example, a turbojet engine, a turbofan engine, a turboprop engine, etc.
- a performance enhancing aspirator apparatus 100 mounted on a turbofan gas turbine 101 engine is exemplarily illustrated.
- a turbofan gas turbine 101 engine would require a convergent duct 104 because of the subsonic exhaust produced by the turbofan gas turbine 101 engine, in an embodiment, a Turbojet gas turbine 101 engine will require a convergent-divergent duct because of the supersonic exhaust produced,
- FIG. 2 exemplarily illustrates a front elevation view of a performance enhancing aspirator apparatus 100.
- the performance enhancing aspirator apparatus 100 is mounted on the exterior surface 101a of the gas turbine 101 as exemplarily illustrated in FIGS. 1- 2.
- the attachment members 102 are positioned radially on an exterior surface 101a of the gas turbine 101.
- the substantially funnel shaped casing 103 is fixedly attached to the exterior surface 101a of the gas turbine 101 via the attachment members 102.
- the substantially funnel shaped casing 103 draws in surplus air from the atmosphere using vacuum which is produced due to the design and area of installation of the performance enhancing aspirator apparatus 100.
- the exhaust gases coming out of the nozzle 105 of the gas turbine 101 is then passed through the performance enhancing aspirator apparatus 100, where it is accelerated to very high velocities as exemplarily illustrated in FIG. 1.
- This increase in velocity of exhaust gases results in drop of pressure after the nozzle 105 section of the gas turbine 101. Due to this low pressure created in the converging duct 104, surplus high-pressure atmospheric air is drawn in automatically through the performance enhancing aspirator apparatus 100.
- This surplus air is accelerated in the converging duct 104 and exits through the nozzle .105 with the exhaust gases of the gas turbine 101 at very high velocities. This increases the mass flow of air exiting through the nozzle 105, ultimately increasing the thrust produced by the gas turbine 101.
- the performance enhancing aspirator apparatus 100 contribute toward a reduction in operating costs.
- the main gas turbine 101 of an aircraft fails midflight, then the main fan disk is rotated by using an electric motor as a backup to generate some amount of thrust via a bypass duct.
- the performance enhancing aspirator apparatus 100 draws in extra air using the bypass exhaust of the gas turbine 101, the aircraft will be able to reach the nearest landing strip.
- the performance enhancing aspirator apparatus 100 used will be convergent because the bypass exhaust of the gas turbine 101 is at subsonic speed and it needs a convergent duct 104 to accelerate as exemplarily illustrated in FIG. 1.
- the increased acceleration of the bypass exhaust will create the vacuum required.
- the core exhaust of the gas turbine 101 is untouched and it is not accelerated.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1912023.7A GB2573481A (en) | 2017-01-25 | 2017-04-24 | Performance enhancing aspirator apparatus |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IN201721002895 | 2017-01-25 | ||
IN201721002895 | 2017-01-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2018138730A1 true WO2018138730A1 (en) | 2018-08-02 |
Family
ID=62978145
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IN2017/000091 WO2018138730A1 (en) | 2017-01-25 | 2017-04-24 | Performance enhancing aspirator apparatus |
Country Status (2)
Country | Link |
---|---|
GB (1) | GB2573481A (en) |
WO (1) | WO2018138730A1 (en) |
-
2017
- 2017-04-24 GB GB1912023.7A patent/GB2573481A/en not_active Withdrawn
- 2017-04-24 WO PCT/IN2017/000091 patent/WO2018138730A1/en active Application Filing
Non-Patent Citations (1)
Title |
---|
P. K. NAG, PUBLISHED ON, 31 December 2002 (2002-12-31), pages 549 - 551, ISBN: 0-07-047338-2 * |
Also Published As
Publication number | Publication date |
---|---|
GB201912023D0 (en) | 2019-10-02 |
GB2573481A (en) | 2019-11-06 |
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