GB2263313A - Turbocharger with exhaust gas cooling. - Google Patents
Turbocharger with exhaust gas cooling. Download PDFInfo
- Publication number
- GB2263313A GB2263313A GB9124177A GB9124177A GB2263313A GB 2263313 A GB2263313 A GB 2263313A GB 9124177 A GB9124177 A GB 9124177A GB 9124177 A GB9124177 A GB 9124177A GB 2263313 A GB2263313 A GB 2263313A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbo charger
- engine
- compressor
- exhaust
- turbine
- 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
- 238000001816 cooling Methods 0.000 title 1
- 239000007789 gas Substances 0.000 claims abstract description 13
- 238000010276 construction Methods 0.000 claims description 6
- 238000001514 detection method Methods 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000001473 noxious effect Effects 0.000 description 1
- 230000003584 silencer Effects 0.000 description 1
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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C18/00—Rotary-piston pumps specially adapted for elastic fluids
- F04C18/02—Rotary-piston pumps specially adapted for elastic fluids of arcuate-engagement type, i.e. with circular translatory movement of co-operating members, each member having the same number of teeth or tooth-equivalents
- F04C18/0207—Rotary-piston pumps specially adapted for elastic fluids of arcuate-engagement type, i.e. with circular translatory movement of co-operating members, each member having the same number of teeth or tooth-equivalents both members having co-operating elements in spiral form
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
An engine turbo charger (10) comprises a compressor (12) and a turbine (14), the compressor (12) being driven by exhaust gases from the engine (18), the compressor (12) being arranged to compress two flows of compressed air in parallel, a first flow through duct (20) at a higher pressure to turbo charge the engine (18) in the normal manner and a second flow at a lower pressure through the duct (28) which is arranged to be delivered to the exhaust from the turbo charger turbine (14). <IMAGE>
Description
Turbo Charger
The present invention relates to a turbo charger for an internal combustion engine.
In particular the invention relates to a turbo charger which is designed to reduce the exhaust temperature and the infra-red signature of an internal combustion engine.
On military vehicles especially tanks there is need to reduce the vulnerability of the vehicle to infra-red detection. In order to reduce the infra-red signature of the vehicle the temperature of the exhaust gases from the engine turbo charger should be minimised and means provided for baffling the exhaust ducting from the turbo charger so that the hot metal components within the turbine of the turbo charger are not visible to infra red detection.
This present invention seeks to provide a turbo charger in which a considerable reduction in the exhaust gas temperature from the turbo charger is achieved and the turbine of the turbo charger is concealed from infra red detection.
Accordingly the present invention provides an engine turbo charger comprising a compressor and a turbine, the turbine being driven by exhaust gases from the engine, the compressor being arranged to compress two flows of compressed air in parallel, a first flow at a higher pressure to turbo charge the engine in the normal manner and a second flow at a lower pressure which is arranged to be delivered to the exhaust from the turbo charger turbine.
The compressor preferably has a stepped diameter centrifugal rotor with two distinct tip diameters, in order to compress the two compressed air flows.
The turbo charger turbine can have a mixer and an exhaust duct of double skin construction, the mixer and space between the skins being supplied with the second lower pressure flow of air from the compressor of the turbo charger. The exhaust duct can include a 900 bend and can have cooled, radial baffles at the exit of the exhaust duct.
The flow rates of the higher and lower pressure air flows from the turbo charger compressor can be chosen to be equal if desired, or such as to give a particular selected mixed exhaust temperature from the turbo charger. exhaust.
The present invention will now be more particularly described with reference to the accompanying drawings in which;
Figure 1 shows a diagrammatic side elevation of one form of turbo charger according to the present invention;
Figure 2 is a view looking into the exhaust of the turbo charger shown in Figure 1.
Referring to the drawings a turbo charger (10) comprises a compressor (12) and a turbine (14) mounted on a common shaft (16).
The turbo charger (10) is connected to an engine (18) by means of a duct (20) which extends 'between the compressor (12) and an inlet manifold (22) of the engine (18), and an exhaust duct (24) which extends from an exhaust manifold outlet (26) of the engine (18) to the inlet of the turbine (14).
A duct (28) also extends from the compressor (12) of the turbo charger (10) to an exhaust mixer (30) which is located downstream of the outlet from the turbine (14).
The compressor (12) comprises a housing (12A) and a stepped diameter centrifugal rotor (12B). The rotor (12B) has a larger diameter D, at which the duct (20) is connected and a smaller diameter D2 at which the duct (28) is connected.
The ducts or volute casings (20) and (28) are connected to the compressor (12) of the turbo charger (10) at locations so that the flows through the ducts (20 and 28) are at different pressures, the pressure in the duct (20) being greater than the pressure in the duct (28) by virtue of the stepped rotor design.
Preferably though not necessary the flow rates in the ducts (20) and (28) can be approximately equal.
A row (32) of stationary outlet guide vanes (34) to direct the gas flow axially is located between the outlet of the turbine (14) and the inlet to the mixer (30). The mixer (30) is attached to an exhaust duct (36) which is of doubled walled constructed and which terminates in radial baffles (38). The exhaust duct (36) includes a 90 bend (42).
The mixer (30) comprises a number of radial lobes (30A and 30B).
The exhaust gases from the turbine (14) of the turbo charger (10) are arranged to flow through the lobes (30A) whilst the compressed air flows from the compressor (12) of the turbo charger (10) which flow through the duct (28) is arranged to flow through the lobes (30B) so that the lower temperature air from the compressor (12) mixes efficiently with the high temperature exhaust gases from the turbine (14). The construction of the mixer (30) is similar to the construction of a mixer for an aircraft gas turbine engine silencer.
The turbine (14) can be of conventional design with fixed geometry, but preferably having a variable inlet nozzle (14A) which can be of the type described and claimed in my European patent number 0 212 834 the contents of which are hereby incorporated by reference.
In operation the turbo charger (10) delivers compressed air through the duct (20) to the inlet manifold (22) of the engine (18). Exhaust gases from the engine flow through the exhaust manifold (26), the duct (24), the fixed or the variable nozzle (14A) into the turbine (14) which drives the compressor (12) through the shaft (16).
The engine exhaust gases pass through the turbine rotot (14) into the mixer (30) where they mix with the relatively low pressure air delivered from the compressor (12), through the duct (28) and through the lobes (30B) of the mixer (30).
The relatively cool low pressure air from the compressor (12) also flows into the space between the two skins of the exhaust duct (36) and also into the radial baffles (38).
The arrangement according to the invention as described above reduces considerably the temperature of the exhaust gases from the turbo charger (10) by mixing the relatively low pressure air from the compressor (12) with the exhaust gases from the turbine (14), this low pressure air also being used to cool the exhaust duct (36) itself.
The relatively high temperature components of the turbine (14) are also rendered invisible to infra red detection by virtue of the 90O bend (42) in the exhaust duct (36), and cooled radial baffles (38).
If the variable nozzle (14A) is of the construction as described and claimed in my European patent number 0 212 834, it is expected that there will be also a reduction in noxious exhaust emissions and that the engine output torque will be increased at lower engine speeds whilst also increasing engine power and fuel economy at high engine speeds.
Claims (10)
1. An engine turbo charger comprising a compressor and a
turbine, the turbine being driven by exhaust gases from the
engine, the compressor being arranged to compress two flows
of compressed air in parallel, a first flow at a higher
pressure to turbo charge the engine in the normal manner
and a second flow at a lower pressure which is arranged to
be delivered to the exhaust from the turbo charger turbine.
2. An engine turbo charger as claimed in claim 1 in which the
compressor has a stepped diameter centrifugal rotor with
two distinct tip diameters in order to compress the two
compressed air flows.
3. An engine turbo charger as claimed in claim 1 or claim 2 in
which the turbo charger turbine includes a mixer and an
exhaust duct.
4. An engine turbo charger as claimed in claim 3 in which the
exhaust duct is of a double skin construction.
5. An engine turbo charger as claimed in claim 4 in which the
mixer and the space between the skins of the double skin
construction exhaust duct are supplied with the second
lower pressure flow of air from the compressor of the turbo
charger.
6. An engine turbo charger as claimed in claim 3 in which the
exhaust duct includes a 90O bend.
7. An engine turbo charger as claimed in claim 3 in which the
outlet of the exhaust duct includes cooled radial baffles.
8. An engine turbo charger as claimed in any one of the
preceding claims in which the flow rates of the higher and
lower pressure air flows from the turbo charger compressor
are approximately equal.
9. An engine turbo charger as claimed in any one of the
preceding claims 1 to 7 in which the flow rates of the
higher and lower pressure air flows from the turbo charger
compressor are chosen to give a particular selected mixed
exhaust temperature from the turbo charger exhaust.
10. An engine turbo charger constructed and arranged for use
and operation substantially as hereinbefore described, and
with reference to the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9124177A GB2263313B (en) | 1991-11-14 | 1991-11-14 | Turbo charger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9124177A GB2263313B (en) | 1991-11-14 | 1991-11-14 | Turbo charger |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9124177D0 GB9124177D0 (en) | 1992-07-22 |
| GB2263313A true GB2263313A (en) | 1993-07-21 |
| GB2263313B GB2263313B (en) | 1994-11-09 |
Family
ID=10704611
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9124177A Expired - Fee Related GB2263313B (en) | 1991-11-14 | 1991-11-14 | Turbo charger |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2263313B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103438026A (en) * | 2013-09-09 | 2013-12-11 | 中国航空动力机械研究所 | Centrifugal air compressor with intermediate-stage air entrainment function |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB520045A (en) * | 1937-11-29 | 1940-04-12 | Turbo Engineering Corp | Improvements in or relating to elastic fluid turbines |
| GB549700A (en) * | 1940-10-24 | 1942-12-03 | Turbo Engineering Corp | Improvements in or relating to the propulsion of aircraft or vehicles |
| GB968238A (en) * | 1961-04-04 | 1964-09-02 | Prvni Brnenska Strojirna Zd Y | Improvements in or relating to exhaust-gas driven turbochargers |
| US3866423A (en) * | 1972-06-15 | 1975-02-18 | Wallace Murray Corp | Turbocharger compressor with dual inlet and collector chambers |
-
1991
- 1991-11-14 GB GB9124177A patent/GB2263313B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB520045A (en) * | 1937-11-29 | 1940-04-12 | Turbo Engineering Corp | Improvements in or relating to elastic fluid turbines |
| GB549700A (en) * | 1940-10-24 | 1942-12-03 | Turbo Engineering Corp | Improvements in or relating to the propulsion of aircraft or vehicles |
| GB968238A (en) * | 1961-04-04 | 1964-09-02 | Prvni Brnenska Strojirna Zd Y | Improvements in or relating to exhaust-gas driven turbochargers |
| US3866423A (en) * | 1972-06-15 | 1975-02-18 | Wallace Murray Corp | Turbocharger compressor with dual inlet and collector chambers |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103438026A (en) * | 2013-09-09 | 2013-12-11 | 中国航空动力机械研究所 | Centrifugal air compressor with intermediate-stage air entrainment function |
Also Published As
| Publication number | Publication date |
|---|---|
| GB9124177D0 (en) | 1992-07-22 |
| GB2263313B (en) | 1994-11-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19981114 |