GB2498005A - A Hypersonic Ram/Scramjet - Google Patents
A Hypersonic Ram/Scramjet Download PDFInfo
- Publication number
- GB2498005A GB2498005A GB1200683.9A GB201200683A GB2498005A GB 2498005 A GB2498005 A GB 2498005A GB 201200683 A GB201200683 A GB 201200683A GB 2498005 A GB2498005 A GB 2498005A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas turbine
- text
- electrical energy
- source
- aircraft
- 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.)
- Granted
Links
- 239000007789 gas Substances 0.000 claims abstract description 66
- 239000000446 fuel Substances 0.000 claims abstract description 18
- 239000003225 biodiesel Substances 0.000 claims abstract description 5
- 239000003990 capacitor Substances 0.000 claims abstract description 5
- 239000001257 hydrogen Substances 0.000 claims abstract description 5
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 5
- 239000003350 kerosene Substances 0.000 claims abstract description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 3
- 238000002485 combustion reaction Methods 0.000 claims description 34
- 238000010438 heat treatment Methods 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 230000003190 augmentative effect Effects 0.000 claims description 3
- 238000009429 electrical wiring Methods 0.000 claims description 3
- 125000004435 hydrogen atom Chemical group [H]* 0.000 claims description 2
- SYHGEUNFJIGTRX-UHFFFAOYSA-N methylenedioxypyrovalerone Chemical compound C=1C=C2OCOC2=CC=1C(=O)C(CCC)N1CCCC1 SYHGEUNFJIGTRX-UHFFFAOYSA-N 0.000 claims 1
- 230000005611 electricity Effects 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
A source of electrical energy, which may be from a gas turbine 1 connected to an electrical generator 2, provides electricity to heat air of a ram/scramjet 3 using such means as electric arcs using electrodes 4. The source of electrical energy may also be from solar panels or fuel cells or capacitors. The gas turbine may be powered using hydrogen or kerosene or biodiesel and may also function as a turbojet, with or without afterburning, using a clutch. The ram/scramjets may be positioned near the generator to keep wiring to a minimum. The gas turbine may be positioned near the rear of the aircraft to enable the oncoming high speed airflow to be slowed down, and there may be a large air reservoir (7, fig 4) connected an intake (6) which may vary in size.
Description
A Hypersonic Ram/Scraiujet This invention relates to a method of heating for ram/scramjets which enables them to have a better performance at high Mach numbers.
Scramjets, when operating at high Mach numbers, suffer from the compressed air being so hot that the fuel is unable to add much heat, and thus generate much thrust. If there was less compression the fuel would also be liable to complete combustion downstream of the combustion chamber and outside of the engine, both these resulting in poor performance at high Mach numbers. To overcome this, the present invention proposes at least one source of electrical energy, said source of electrical energy used to heat air in at least one rarn/scramjet.
When the air is heated using the source of electrical energy a much higher temperature can be achieved than the combustion of fuel, and heating is much more likely to remain in the combustion chamber enabling higher speeds to be attained.
Preferably, said source of electrical energy is an electric generator.
Preferably, said electric generator is powered by a gas turbine.
Preferably, said heating of air in said ram/scramjet is by electric arcs.
Preferably, said gas turbine consumes air from the atmosphere.
Preferably, said gas turbine operates as a turbojet, with or without afterburning, to propel an aircraft up to ram/scranjet operating speeds, connecting and disconnecting from said electric generator by means of a clutch.
Preferably, said air supply powering said gas turbine is slowed before entering said gas turbine at high speeds.
Preferably, said source of electrical energy is fuel cells, cells or capacitors.
Preferably, said source of electrical energy is solar panels.
Preferably, fuel of said gas turbine is hydrogen or kerosene or bio diesel.
Preferably, said gas turbine and said ram/scramjets are positioned close to each other to minimise electrical wiring.
Preferably, said gas turbine is positioned towards the rear of said aircraft to allow oncoming air to be slowed down for its intake.
Preferably, said intake leads to an enclosed large area prior to said gas turbine intake which acts as an air reservoir and a velocity sink. 2!
Preferably, said intake area is variable to allow different amounts of air in at different altitudes and/or speeds.
Preferably, there are at least two or more sources of electrical energy.
Preferably, there are at least two or more ram/scranjets.
Preferably, said aircraft is thrust augmented by a solid or liquid fuelled rocket to enable propulsion where the air is too thin or in space.
Preferably, said fuel is circulated around said scranjet to keep it cool and then fed into said gas turbine.
Preferably, said generator has two or more gears to enable a higher rpm.
Preferably, said gas turbine has at least one combustion chamber after the first turbine stage/stages leading to a second turbine stage/stages to enable extra shaft power from a type of afterburning.
Preferably, said gas turbine has two or more combustion chambers and turbine stage/stages after said first turbine stageistages.
An example of the invention will now be described by referring to the accompanying drawings: -figure 1 shows a side view of a hypersonic ram/scramjet; and -figure 2 shows a side view of a hypersonic ram/scramjet on an aircraft; and -figure 3 shows a front view of a hypersonic ram/scramjet on an aircraft; and -figure 4 shows a top view of a hypersonic ram/scramjet on an aircraft; and -figure 5 shows a side view of a hypersonic ran/scranjet on an aircraft according to the invention.
A source of electrical energy which nay be from a turbo generator such as a gas turbine 1 connected to an electrical generator 2 provides electricity to heat air in the combustion chamber of a ram/scranjet 3 using such means as electric arcs using electrodes 4. The source of electrical energy may also be from solar panels or fuel cells or cells or capacitors. The gas turbine may be powered using hydrogen or kerosene or biodiesel and the ran!scramjets may be positioned close to the generator to keep wiring to a minimum. The gas turbine may be positioned near the rear of an aircraft to enable the oncoming high speed airflow to be slowed down for it 5.
H
A variable air intake 6 may lead to a large enclosed area 7 which acts as an air reservoir and a velocity sink. In operation, from the moment the aircraft is moving the air reservoir will be full and at high speeds the incoming high velocity air will impact the air in the reservoir and be slowed down creating a suitable pressure for the gas turbine. Preferably at high velocities and appropriate air densities the intake area to the reservoir will be smaller than the exit out of the reservoir through the gas turbines.
The gas turbines may also operate as turbojets with or without afterburning to enable the aircraft to reach velocities in which the ram/scramjets can function. A solid or liquid fuelled rocket may be used to propel the aircraft where the air is too thin or in space.
Fuel may be circulated around the scramjet to keep it cool and then fed into the gas turbine. The generator may have two or more gears to enable a higher rpm once the generator has reached its maximum rpm under the power of the gas turbine.
With no requirements for a specific voltage, current, frequency or phase of the output of the electrical generator other than to power the ram/scramjets, the generator can be designed to be as light as possible for flight.
The demands for shaft power fron the gas turbine will be high, and burning more fuel in the combustion chamber would place high demands on the turbine blades due to the extra heat and straightening force, so preferably one or more extra combustion chambers 8 and turbine sets 9 after the first combustion chamber and turbine sets would enable a gradual extraction of energy from the available air supply and fuel mix with the extra turbine sets sharing the load.
The exhaust from each turbine stage, including the first one, would be slightly lower in temperature and pressure than the earlier combustion chamber allowing more fuel to be added without overloading the following turbine stages.
Claims (1)
- <claim-text>Claims 1 At least one source of electrical energy, said source of electrical energy used to heat air in at least one ramlscramjet.</claim-text> <claim-text>2 At least one source of electrical energy according to claim 1, wherein said source of electrical energy is an electric generator.</claim-text> <claim-text>3 At least one source of electrical energy according to claim 2, wherein said electric generator is powered by a gas turbine.</claim-text> <claim-text>4 At least one source of electrical energy according to any of the preceding claims, wherein said heating of air in said rarn/scramjet is by electric arcs.</claim-text> <claim-text>At least one source of electrical energy according to claim 3, wherein said gas turbine consumes air from the atmosphere.</claim-text> <claim-text>6 At least one source of electrical energy according to claim 5, wherein said gas turbine operates as a turbojet to propel an aircraft up to ram/scramjet operating speeds, connecting and disconnecting from said electric generator by means of a clutch.</claim-text> <claim-text>7 At least one source of electrical energy according to claim 6, wherein said air supply powering said gas turbine is slowed before entering said gas turbine at high speeds.</claim-text> <claim-text>8 At least one source of electrical energy according to any of the preceding claims, wherein said source of electrical energy is fuel cells, cells or capacitors.</claim-text> <claim-text>9 At least cne source of electrical energy according to any of the preceding claims, wherein said source of electrical energy is solar panels.</claim-text> <claim-text>At least one source of electrical energy according to claim 7, wherein fuel of said gas turbine is hydrogen or kerosene or bio diesel.</claim-text> <claim-text>11 At least one source of electrical energy according to claim 10, wherein said gas turbine and said raxn/scramjets are positioned close to each other to minimise electrical wiring.</claim-text> <claim-text>12 At least one source of electrical energy according to claim 11, wherein said gas turbine is positioned towards the rear of said aircraft to allow oncoming air to be slowed down for its intake.</claim-text> <claim-text>13 At least one source of electrical energy according to claim 12, wherein said intake leads to an enclosed large area prior to said gas turbine intake which acts as an air reservoir and a velocity sink.</claim-text> <claim-text>14 At least one source of electrical energy according to claim 13, wherein said intake area is variable to allow different amounts of air in at different altitudes and/or speeds.</claim-text> <claim-text>At least one source of electrical energy according to any of the preceding claims, wherein there are at least two or more sources of electrical energy.</claim-text> <claim-text>16 At least one source of electrical energy according to any of the preceding claims, wherein there are at least two or more ram/scramjets.</claim-text> <claim-text>17 At least one source of electrical energy according to claim 14.wherein said aircraft is thrust augmented by a solid or liquid fuelled rocket to enable propulsion where the air is too thin or in space.</claim-text> <claim-text>18 At least one source of electrical energy according to claim 10, wherein said fuel is circulated around said scramjet to keep it cool and then fed into said gas turbine.</claim-text> <claim-text>19 At least one source of electrical energy according to claim 3, wherein said generator has two or more gears to enable a higher rpm.</claim-text> <claim-text>At least one source of electrical energy according to claim 10, wherein said gas turbine has at least one combustion chamber after the first turbine stage/stages leading to a second turbine stage/stages to enable extra shaft power from a type of afterburning.</claim-text> <claim-text>21 At least one source of electrical energy according to claim 20, wherein said gas turbine has two or more combustion chambers and turbine stage/stages after said first turbine stage/stages.Amendments to the claims have been filed as follows Claims 1 An aircraft comprising a gas turbine engine and a ram/scranjet combustion chamber, wherein said gas turbine powers an electric generator which provides at least one source of electrical energy1 wherein said source of electrical energy is used to heat air in said combustion chamber of said ram/scramjet, wherein said heating of air in said ramlscramjet is by electric arcs.2 The aircraft comprising a gas turbine engine and a ramlscramjet combustion chamber according to claim 1, wherein said gas turbine consumes air from the atmosphere.3 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 2, wherein said gas turbine operates as a turbojet to propel said aircraft up to ram/scraTniet operating speeds, connecting and disconnecting from said electric generator by means of a clutch.4 The aircraft comprising a gas turbine engine and a ram/scralnjet combustion chamber according to claim 3, wherein said air supply powering said gas turbine is slowed before entering said gas turbine at high speeds.The aircraft comprising a gas turbine engine and a ram/scramiet combustion chamber according to claim 1, wherein said source of electrical energy is fuel cells, cells or capacitors.6 The aircraft comprising a gas turbine engine and a ramlscranijet combustion chamber according to claim 1, wherein said source of electrical energy, is solar panels.7 The aircraft comprising a gas turbine engine and a ram/scranijet combustion chamber according to claim 4, wherein fuel cf said gas turbine * is hydrogen or kerosene or bio diesel. *0*s*B The aircraft comprising a gas turbine engine and a ram/scranhiet combustion chamber according to claim 7, wherein said gas turbine and said ram/scramjets are positioned close to each other to minimise * electrical wiring.9 The aircraft comprising a gas turbine engine and a ranilscramjet ". : combustion chamber according to claim 8, wherein said gas turbine is positioned towards the rear of said aircraft to allow oncoming air to be *. slowed down for its intake.The aircraft comprising a gas turbine engine and a ram/scrainjet combustion chamber according to claim 9, wherein said intake leads to an enclosed large area prior to said gas turbine intake which acts as an air reservoir and a velocity sink.11 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 10, wherein said intake area is variable to allow different amounts of air in at different altitudes and/or speeds.12 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to any of the preceding claims, wherein there are at least two or more sources of electrical energy.13 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to any of the preceding claims, wherein there are at least two or more ram/scramjets.14 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 11, wherein said aircraft is thrust augmented by a solid or liquid fuelled rocket to enable propulsion where the air is too thin or in space.The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 7, wherein said fuel is circulated around said scramjet to keep it cool and then fed into said gas turbine.16 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 1, wherein said generator has two or more gears to enable a higher rpm.17 The aircraft comprising a gas turbine engine and a ram/scramjet combustion chamber according to claim 7, wherein said gas turbine has at least one combustion chamber after the first turbine stage/stages leading to a second turbine stage/stages to enable extra shaft power from a type of afterburning.lB The aircraft comprising a gas turbine engine and a ram!scramjet combustion chamber according to claim 17, wherein said gas turbine has r.". two or more combustion chambers and turbine stage/stages after said first * turbine stage/stages. * * * **I ** S * I S * SIIS</claim-text>
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GBGB1122512.5A GB201122512D0 (en) | 2011-12-31 | 2011-12-31 | A hypersonic ram/scramjet |
| GBGB1200304.2A GB201200304D0 (en) | 2011-12-31 | 2012-01-09 | A hypersonic ram/scramjet |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB201200683D0 GB201200683D0 (en) | 2012-02-29 |
| GB2498005A true GB2498005A (en) | 2013-07-03 |
| GB2498005B GB2498005B (en) | 2013-12-25 |
Family
ID=45755648
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB1122512.5A Ceased GB201122512D0 (en) | 2011-12-31 | 2011-12-31 | A hypersonic ram/scramjet |
| GBGB1200304.2A Ceased GB201200304D0 (en) | 2011-12-31 | 2012-01-09 | A hypersonic ram/scramjet |
| GB1200683.9A Expired - Fee Related GB2498005B (en) | 2011-12-31 | 2012-01-16 | A hypersonic ram/scramjet |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB1122512.5A Ceased GB201122512D0 (en) | 2011-12-31 | 2011-12-31 | A hypersonic ram/scramjet |
| GBGB1200304.2A Ceased GB201200304D0 (en) | 2011-12-31 | 2012-01-09 | A hypersonic ram/scramjet |
Country Status (1)
| Country | Link |
|---|---|
| GB (3) | GB201122512D0 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2607638A (en) * | 2021-06-09 | 2022-12-14 | Desmond Stephen Lewis | Propulsion for aerospace applications |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB696757A (en) * | 1950-02-14 | 1953-09-09 | Nat Res Dev | Apparatus for burning liquid fuel in a ducted gas stream |
| GB950629A (en) * | 1959-05-12 | 1964-02-26 | Raytheon Co | Microwave jet propulsion engines |
| US3509568A (en) * | 1968-07-08 | 1970-04-28 | North American Rockwell | Inlet attenuator assembly |
| US3841090A (en) * | 1971-10-22 | 1974-10-15 | T Sharpe | Jet engine method |
| US4778130A (en) * | 1986-05-08 | 1988-10-18 | Kyusik Kim | Ultra hypersonic aircraft |
| US6527221B1 (en) * | 2000-05-31 | 2003-03-04 | Kevin Kremeyer | Shock wave modification method, apparatus, and system |
| EP2312126A1 (en) * | 2009-10-08 | 2011-04-20 | General Electric Company | Power generation system and corresponding power generating method |
-
2011
- 2011-12-31 GB GBGB1122512.5A patent/GB201122512D0/en not_active Ceased
-
2012
- 2012-01-09 GB GBGB1200304.2A patent/GB201200304D0/en not_active Ceased
- 2012-01-16 GB GB1200683.9A patent/GB2498005B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB696757A (en) * | 1950-02-14 | 1953-09-09 | Nat Res Dev | Apparatus for burning liquid fuel in a ducted gas stream |
| GB950629A (en) * | 1959-05-12 | 1964-02-26 | Raytheon Co | Microwave jet propulsion engines |
| US3509568A (en) * | 1968-07-08 | 1970-04-28 | North American Rockwell | Inlet attenuator assembly |
| US3841090A (en) * | 1971-10-22 | 1974-10-15 | T Sharpe | Jet engine method |
| US4778130A (en) * | 1986-05-08 | 1988-10-18 | Kyusik Kim | Ultra hypersonic aircraft |
| US6527221B1 (en) * | 2000-05-31 | 2003-03-04 | Kevin Kremeyer | Shock wave modification method, apparatus, and system |
| EP2312126A1 (en) * | 2009-10-08 | 2011-04-20 | General Electric Company | Power generation system and corresponding power generating method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2607638A (en) * | 2021-06-09 | 2022-12-14 | Desmond Stephen Lewis | Propulsion for aerospace applications |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2498005B (en) | 2013-12-25 |
| GB201122512D0 (en) | 2012-02-15 |
| GB201200683D0 (en) | 2012-02-29 |
| GB201200304D0 (en) | 2012-02-22 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 746 | Register noted 'licences of right' (sect. 46/1977) |
Effective date: 20150603 |
|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20240116 |