GB2565761A - Combustion engine fuel mixture system - Google Patents
Combustion engine fuel mixture system Download PDFInfo
- Publication number
- GB2565761A GB2565761A GB1712206.0A GB201712206A GB2565761A GB 2565761 A GB2565761 A GB 2565761A GB 201712206 A GB201712206 A GB 201712206A GB 2565761 A GB2565761 A GB 2565761A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fuel
- combustion chamber
- combustion engine
- ring
- series
- 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.)
- Withdrawn
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
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
Abstract
A combustion engine, preferably a turbojet engine 1, is provided with one or more fuel mixture systems which each comprise a combustion chamber 13 with a housing having inlets 14, and also an aperture inlet 15 with a restriction device, typically of variable size for controlling the air intake according to operating conditions. A circumferential ring 16, typically around inlet 15, is also provided which may have either a series of fuel outlets into chamber 13, or alternatively a single fuel outlet. An alternative arrangement has both an internal fuel ring and an external fuel ring. One example has a series of fuel outlets in circumferential ring 16 that are not of constant size. The arrangement may reduce fuel consumption while increasing power.
Description
Description of Invention
Field of the Invention
The present invention relates to a Combustion Engine Fuel Mixture System internal to Turbo Jet Engine. Turbo Jet Engines are used in commercial and military aeroplanes, helicopters and generators, presently environmental concerns and governments are putting ever increasing pressure on engine manufacturers to drive down emissions of their engines and increase fuel economy. The market is also putting pressure on airlines to provide longer haul flights without stoppages. This invention targets these issues by reducing fuel consumption whilst increasing power.
Statements of Invention
Accordingly, the present invention is directed, but not solely to a Turbo Jet Combustion Engine. Said Turbo Jet Assembly consisting of a set of Engine Cases, said Engine Cases house a Compressor comprising of a Compressor Blade Housing and Compressor Blades which is fixed to a rotating Shaft, said Shaft is located on Bearings which are housed inside a Hub. Said Hub is fixed internal to said Engine Cases via Support Members. During operation said Compressor is driven by a Turbine consisting of a Turbine Blade Housing and Turbine Blades, said Turbine rotates due to Exhaust Gases which are created by combustion in a Combustion Chamber, in the first embodiment of the invention there are multiple Combustion Chambers located around said Hub between said Compressor and said Turbine. Said Combustion Chambers are located between said Compressor and Said Turbine. During operation said Compressor compresses air into said Combustion Chamber via a series of Combustion
Chamber Inlets located creating continuous combustion which is expelled down a Combustion Chamber Exhaust into said Turbine. Fuel is supplied to said Combustion Chamber via a Circumferential Ring with either Singular or Multiple Fuel Outlets. Said Circumferential Ring has an Aperture Inlet inside which supplies compressed air supplied by said Compressor. The flow rate of compressed air supplied through the Aperture Inlet is controlled by a Restriction device. Compressed Air flow through the centre of the fuel delivery system named as the Circumferential Ring is the main embodiment of this invention. In the second embodiment of the invention there is one Combustion Chamber with an Inner Case and an Outer Case. Said Inner Case and said Outer Case have multiple Combustion Chamber Inlets creating continuous combustion down the combustion Chamber Exhaust. Fuel is supplied via multiple Circumferential Rings with Aperture Inlets with either Singular or Multiple Fuel Inlets
Preferably the Restriction Device is controlled in relation to the operating conditions of the Turbo Jet Engine.
Brief Description of the Drawings
The accompanying drawings are as follows:
Figure 1 is a side section view of a first embodiment of the Combustion Engine Fuel Mixture System in accordance with the present invention;
Figure 2 is a detailed view of the first embodiment of the invention showing the design details of the Combustion Engine Fuel Mixture System;
Figure 3 is a detailed section view of the first embodiment of the invention showing the design details of the Circumferential Ring with a Singular Fuel Inlet of the Combustion Engine Fuel Mixture System;
Figure 4 is a detailed section view of the first embodiment of the invention showing the design details of the Circumferential Ring with Multiple Fuel Inlets of the Combustion Engine Fuel Mixture System;
Figure 5 is a view of the second embodiment of the invention showing the design details of the Parallel Circumferential Ring with Multiple Inlets of a Single Combustion Chamber Turbo Jet Engine Fuel Mixture System;
Figure 6 is a detailed view of the second embodiment of the invention showing the design details of multiple Circumferential Rings in a Single Combustion Chamber Turbo Jet Engine Fuel Mixture System;
Figure 7 is a view of the third embodiment of the invention showing the design details of the Parallel Circumferential Ring for a Single Combustion Chamber Turbo Jet Engine Fuel Mixture System;
Figure 8 is a detailed section view of the third embodiment of the invention showing the design details of the Parallel Circumferential Ring for a Single Combustion Chamber Turbo Jet Engine Fuel Mixture System with Multiple Fuel Inlets;
Figure 9 is a detailed section view of the third embodiment of the invention showing the design details of the Parallel Circumferential Ring with Singular Inlets of a Single Combustion Chamber Turbo Jet Engine Fuel Mixture System;
Detailed Description of the Invention
The invention will now be described, by way of examples only, with reference to the accompanying drawings.
Referring to Fig. 1 of the accompanying drawings, there is shown a Turbo Jet Engine (1), said Turbo Jet Engine is comprised of a Shaft (2) which rotates on Bearings (3) located in a Hub(4) which is fixed to the Turbo Jet Engine Cases (5). Located on the Inlet (6) side of the Turbo Jet Engine there is a Nose Cone (7) which is connected to the Compressor Blade Housing (8). The Compressor Blade Housing is connected to said Shaft and houses the Compressor Blades (9). Located in the Turbo Jet Exhaust (10) is a Turbine Blade Housing (11) which houses the Turbine Blades (12). Between said Compressor Housing, said Compressor Blades and said Turbine Blade Housing, said Turbine Blades is a Combustion Chamber (13), said Combustion Chamber has Inlets (14) which are supplied with compressed air by said Compressor Blades. There is a Aperture Inlet (15) which is also supplied with compressed air by said Compressor Blades however the size of said Aperture Inlet is variable depending upon operating conditions. Located around said Aperture Inlet is a Circumferential Ring (16) which supplies fuel to said Combustion Chamber via an Fuel Inlet Pipe (17). During operation the fuel and compressed air combust expelling products through the Combustion Chamber Exhaust (18) which drives said Turbine Blades which are connected to Said Turbine Blade Housing which is connected to said Shaft which rotates inside said Bearings, said Shaft is connected to said Compressor Blade Housing which is connected to said Compressor which compresses air through said Turbo Jet Engine Cases into said Combustion Chamber.
Referring to Fig. 2 of the accompanying drawings, there is shown a Combustion Chamber (19) which is constructed with a Combustion Chamber Housing (20) with multiple Compressed Air Inlets (21). There is an Aperture Inlet (22) which has a varied compressed air supply by way of Restriction Device (23), located around said Restriction Device is a Circumferential Ring (24) which has multiple Fuel Outlets (25) which spray Fuel (26) into said Combustion Chamber. Said Fuel is supplied to said Circumferential Ring via a Fuel Inlet Pipe (27). Said Combustion Chamber has a Combustion Chamber Exhaust (28).
Referring to Fig. 3 of the accompanying drawings, there is shown Circumferential Ring (29) which supplied fuel via a Fuel Inlet Pipe (30). Compressed air is supplied through the Aperture Inlet (31). Said Circumferential Ring has a Singular Fuel Outlet (32) which delivers Fuel (33) to the Combustion Chamber (34) where is mixes and combusts with more compressed air which is supplied by multiple Inlets (35). Said Singular Fuel Outlet has a thickness (X).
Referring to Fig. 4 of the accompanying drawings, there is shown Circumferential Ring (36) which supplied fuel via a Fuel Inlet Pipe (37). Compressed air is supplied through the Aperture Inlet (38). Said Circumferential Ring has Multiple Fuel Outlets (39) which deliver Fuel (40) to the Combustion Chamber (41) where is mixes and combusts with more compressed air which is supplied by multiple Inlets (42). Said Multiple Fuel Outlets have a diameter (T).
Referring to Fig. 5 of the accompanying drawings, there is shown a Turbo Jet Combustion Engine (43) with an Inlet (44) and a Turbo Jet Exhaust (45). Turbo Jet
Engine Cases (46) house a Nose Cone (47) which is connected to a Compressor Blade Housing (48) which house Compressor Blades (49). Between said Compressor Blade Housing and the Turbine Blade Housing (50) there is a Hub (51). Connected to said Turbine Blade Housing is the Turbine Blades (52). Located around said Hub is a Single Combustion Chamber (53).
Referring to Fig. 6 of the accompanying drawings, there is shown a Single Combustion Chamber (54) with a Combustion Chamber Housing (55) with multiple Compressed Air Inlets (56) supplying air to the Combustion Chamber (57). Compressed air is also supplied to said Combustion Chamber by the Aperture Inlets (58) which are located inside the Circumferential Rings (59). Said Circumferential Rings are supplied fuel by Fuel Inlet Pipes (60). After combustion of the compressed air and fuel the exhaust gases are expelled out of the Combustion Chamber Exhaust (61).
Referring to Fig. 7 of the accompanying drawings, there is shown a Single Combustion Chamber (62) constructed from a Combustion Chamber Housing (63) with multiple Compressed Air Inlets (64), there is a Aperture Inlet (65) which is also supplied compressed air. Said Aperture Inlet has an Internal Diameter Fuel Ring (66) and an External Diameter Fuel Ring (67) said Internal Diameter Fuel Ring and said External Diameter Fuel Ring are supplied fuel by Fuel Inlet Pipes (68). There are variants of said Internal Diameter Fuel Ring and said External Diameter Fuel Ring shown in Fig. 8 and Fig. 9.
Referring to Fig. 8 of the accompanying drawings, there is shown Internal Diameter Fuel Ring (69) and an External Diameter Fuel Ring (70). Said Internal Diameter Fuel
Ring and said External Diameter Fuel Ring are supplied fuel via Fuel Inlet Pipes (71). Compressed air is supplied to the Combustion Chamber (72) via the Aperture Inlet (73). Said Aperture Inlet has Width (Z) said Width is equal to the radial position difference of said Internal Diameter Fuel Ring and said External Diameter Fuel Ring. Fuel (74) is 5 supplied to said Combustion Chamber via Multiple Fuel Inlets (75).
Referring to Fig. 9 of the accompanying drawings, there is shown Internal Diameter Fuel Ring (76) and an External Diameter Fuel Ring (77). Said Internal Diameter Fuel Ring and said External Diameter Fuel Ring are supplied fuel via Fuel Inlet Pipes (78).
Compressed air is supplied to the Combustion Chamber (79) via the Aperture Inlet (80).
Said Aperture Inlet has Width (Q) said Width is equal to the radial position difference of said Internal Diameter Fuel Ring and said External Diameter Fuel Ring. Fuel (81) is supplied to said Combustion Chamber via Slots (82) in said Internal Diameter Fuel Ring and said External Diameter Fuel Ring, said Slots have a Slot Width (V/).
Claims (13)
1. A Turbo Jet Engine, or alternative Combustion Engine incorporating one or more Combustion Engine Fuel Mixture Systems comprising:
a Combustion Chamber;
a Combustion Chamber Housing;
a series of Compressed Air Inlets;
a Aperture Inlet;
a Circumferential Ring;
a Restriction Device;
a series of Fuel Outlets;
2. A Combustion Engine Fuel Mixture System according to claim 1 wherein Compressed Air is supplied internal to the fuel Delivery System known as the Circumferential Ring.
3. A Combustion Engine Fuel Mixture System according to claim 1 wherein the Fuel supplied to the Combustion Chamber enters via multiple Circumferential Rings containing a series of Fuel Outlets. The Circumferential Rings are located around Aperture Inlets which along with a series of Compressed Air Inlets delivers Compressed Air to the Combustion Chamber.
4. A Combustion Engine Fuel Mixture System according to claim 1 wherein the flow of Compressed Air delivered to the Combustion Chamber through an Aperture Inlet is controlled by a Restriction Device.
5. A Combustion Engine Fuel Mixture System according to claim 1 wherein the series of Fuel Outlets located in the Circumferential Ring(s) are not of a constant size.
6. A Turbo Jet Engine, or alternative Combustion Engine incorporating one or more Combustion Engine Fuel Mixture Systems comprising:
a Combustion Chamber;
a Combustion Chamber Housing;
a series of Compressed Air Inlets;
a Aperture Inlet;
a Circumferential Ring;
a Restriction Device;
a Singular Fuel Outlet;
7. A Combustion Engine Fuel Mixture System according to claim 6 wherein the Circumferential Ring has a Singular Fuel Outlet delivering Fuel to the Combustion Chamber.
8. A Turbo Jet Engine, or alternative Combustion Engine incorporating one or more Combustion Engine Fuel Mixture Systems comprising:
a Combustion Chamber;
a Combustion Chamber Housing;
a series of Compressed Air Inlets;
a Aperture Inlet;
a Internal Diameter Fuel Ring;
a External Diameter Fuel Ring;
a Restriction Device;
a series of Fuel Outlets;
9. A Combustion Engine Fuel Mixture System according to claim 8 wherein the Internal Diameter Fuel Ring supplies Fuel to the Combustion Chamber via a series of Fuel Outlets.
10. A Combustion Engine Fuel Mixture System according to claim 8 wherein the External Diameter Fuel Ring supplies Fuel to the Combustion Chamber via a series of Fuel Outlets.
11. A Turbo Jet Engine, or alternative Combustion Engine incorporating one or more Combustion Engine Fuel Mixture Systems comprising:
a Combustion Chamber;
a Combustion Chamber Housing;
a series of Compressed Air Inlets;
a Aperture Inlet;
a Internal Diameter Fuel Ring;
a External Diameter Fuel Ring;
5 a Restriction Device;
a Singular Fuel Outlet;
12. A Combustion Engine Fuel Mixture System according to claim 11 wherein the Internal Diameter Fuel Ring supplies Fuel to the Combustion Chamber via a
10 Singular Fuel Outlet.
13. A Combustion Engine Fuel Mixture System according to claim 11 wherein the External Diameter Fuel Ring supplies Fuel to the Combustion Chamber via a Singular Fuel Outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1712206.0A GB2565761A (en) | 2017-07-28 | 2017-07-28 | Combustion engine fuel mixture system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1712206.0A GB2565761A (en) | 2017-07-28 | 2017-07-28 | Combustion engine fuel mixture system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201712206D0 GB201712206D0 (en) | 2017-09-13 |
| GB2565761A true GB2565761A (en) | 2019-02-27 |
Family
ID=59778936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1712206.0A Withdrawn GB2565761A (en) | 2017-07-28 | 2017-07-28 | Combustion engine fuel mixture system |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2565761A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1423799A (en) * | 1973-04-12 | 1976-02-04 | Gen Motors Corp | Combustion apparatus |
| GB1536166A (en) * | 1975-04-14 | 1978-12-20 | Phillips Petroleum Co | Combustors |
| US4898001A (en) * | 1984-07-10 | 1990-02-06 | Hitachi, Ltd. | Gas turbine combustor |
| US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
| GB2269660A (en) * | 1988-05-31 | 1994-02-16 | United Technologies Corp | Combustor |
| US20160290649A1 (en) * | 2015-03-31 | 2016-10-06 | Delavan Inc | Fuel nozzles |
-
2017
- 2017-07-28 GB GB1712206.0A patent/GB2565761A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1423799A (en) * | 1973-04-12 | 1976-02-04 | Gen Motors Corp | Combustion apparatus |
| GB1536166A (en) * | 1975-04-14 | 1978-12-20 | Phillips Petroleum Co | Combustors |
| US4898001A (en) * | 1984-07-10 | 1990-02-06 | Hitachi, Ltd. | Gas turbine combustor |
| GB2269660A (en) * | 1988-05-31 | 1994-02-16 | United Technologies Corp | Combustor |
| US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
| US20160290649A1 (en) * | 2015-03-31 | 2016-10-06 | Delavan Inc | Fuel nozzles |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201712206D0 (en) | 2017-09-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |