WO2010010018A1 - Prüfanordnung und prüfsystem für turbolader - Google Patents
Prüfanordnung und prüfsystem für turbolader Download PDFInfo
- Publication number
- WO2010010018A1 WO2010010018A1 PCT/EP2009/059042 EP2009059042W WO2010010018A1 WO 2010010018 A1 WO2010010018 A1 WO 2010010018A1 EP 2009059042 W EP2009059042 W EP 2009059042W WO 2010010018 A1 WO2010010018 A1 WO 2010010018A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbocharger
- line
- gas line
- combustion chamber
- burner
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/042—Testing internal-combustion engines by monitoring a single specific parameter not covered by groups G01M15/06 - G01M15/12
Definitions
- the invention relates to a test arrangement for turbochargers, comprising a combustion chamber with burner insert, which burner insert is connectable to a fuel source, and from which combustion chamber a hot gas line to the turbocharger, as well as with an outgoing from the turbocharger exhaust line with preferably a throttle valve, and a test system for turbocharger, comprising a combustion chamber for receiving a burner insert, which burner insert is connectable to a fuel source, and from which combustion chamber a hot gas line to the turbocharger emanates, and with an outgoing from the turbocharger outlet with preferably a throttle valve.
- the object of the present invention was the further development of such arrangements and systems in order to be able to test in a flexible manner a multiplicity of aggregates under the conditions optimized for this purpose.
- test arrangement described above is inventively characterized in that the burner insert is interchangeable anchored in the combustion chamber.
- the burner and thus also the test arrangement can alternatively be operated with different fuels which are most suitable for the test object.
- a cold gas line leads to the turbocharger, which can be connected to the turbocharger, at least as an alternative to the hot gas line, high temperature gradients can be displayed without permanently switching the burner on and off, which considerably extends the service life of the burner.
- a cold gas line leads to the turbocharger, wherein the mixing ratio is infinitely adjustable via control valves in hot gas and cold gas line. This allows precisely defined temperature profiles to be traced precisely and even with high temperature gradients.
- a particularly advantageous embodiment of the test arrangement according to the invention is further characterized in that the hot gas line branches into two sub-lines leading to one of each two connected turbochargers, and that a cold gas line is provided which branches into two sub-lines, which also to each Weil lead one of two connected turbocharger, each turbocharger is at least alternatively connectable to a partial line of the hot gas line or a partial line of the cold gas line.
- each turbocharger can be connected in steplessly adjustable mixing ratio to one partial line of the hot gas line and one partial line of the cold gas line.
- FIG. 1 shows a schematic representation of a test system according to the invention in a simple embodiment
- FIG. 2 shows an expanded embodiment with possibility of mixing hot and cold gas
- FIG. 3 is a schematic representation of a third embodiment according to the invention.
- the test system of a turbocharger test rig shown in a simple exemplary embodiment in FIG. 1 is used, for example, for the determination of characteristics (thermodynamic characterization) and for specific thermomechanical load tests of exhaust gas turbochargers.
- the turbocharger test stand, far beyond the real vehicle conditions, both sides of the loader with freely selectable, stationary pressure and temperature conditions.
- it can be run test runs for fully automated recording of complete turbine and compressor maps, for automated stuffing and pumping limit detection on the compressor, for manual control and measurement of individual operating points for storage life assessment at adjustable oil pressure and temperature conditions or for burst containment experiments the compressor and turbine housing ,
- the test procedure can be executed fully automated, partially or fully manually. During fully automated test operation, neither manual intervention in the test procedure nor modification of the test parameters is required.
- the turbine side Ia of the turbocharger 1 is acted upon via line 2 with hot gas.
- the burner 3 is controlled by the fuel supply system of the test bench.
- the test bench burner 3 is designed such that its combustion chamber can be alternately equipped with two different, quickly changeable burner inserts 3a, so that different fuels can be used, preferably commercial diesel fuel and CNG (natural gas).
- the hot gas mass flow, pressure and temperature are kept stable within close tolerances, and the control system is controlled by the automation system of the test bench.
- the compressor side Ib of the turbocharger 1 is throttled with a throttle valve 5 to simulate the charge air backpressure caused by the internal combustion engine in real operation.
- the throttle valve 5 is also controlled by the automation system of the test bench. Pressure and temperature are measured in the gas flow before and after the compressor Ib, wherein the mass flow is measured only after the compressor Ib.
- the bearings of the turbocharger 1 are lubricated with oil.
- a conditioning system 6 regulates the temperature, the pressure and, if necessary, the flow of the oil.
- the housing of the turbocharger 1, but at least the compressor side Ib, is flowed through with temperature and volume controlled coolant.
- Fig. 2 shows a schematic representation of a system for fully automated and pairwise life testing of preferably identical turbochargers 1 by means of automated thermal cycles.
- the system illustrated in FIG. 1 and explained above can be expanded by fitting the additional components to the exhaust-gas turbocharger test system according to FIG. 2.
- the targeted driving of thermal gradients during the test run could be realized via an alternating operation of the burner 3 for a test bench with only one turbocharger, but this would have adverse effects on the burner behavior and the service life of the combustion chamber.
- the achievable temperature gradients due to the large thermal mass involved in the change in temperature (burner, combustion chamber, pipe connections) are relatively small and in most cases do not lead to the desired test results.
- the burner 3 can be fired on the power side in quasi-stationary operation, which ensures the long service life of the burner system.
- the cold air is partly passed over the line 4 to the burner 3 and partly via the line 4a on the burner 3 and divided into two lines 4b, 4c, in which switching valves 7 are installed.
- the output 8 of the burner 3 is also divided into two lines 8b, 8c, in which changeover valves 9 are installed and which open behind the changeover valves 7 of the cold gas lines 4b, 4c in this. This results in two divided mass flows with different Licher temperature and different mass flow, which is the turbine side Ia of the two turbochargers 1 is supplied.
- the mass flows are adjusted by the throttle valve 17 so that the energy present in the flow through the turbocharger turbine Ia is largely identical on both sides.
- a switch between hot and cold i.e., switching of the hot gas from one turbine to the other turbine and simultaneously an opposite switching of the cold gas
- quasi free of unwanted state changes of the two turbochargers 1 take place.
- the air flows on both sides of the compressor Ib are guided via blow-off lines 10 and possibly by oil separator in theticianstandsausaugung 11, taking precautions that they do not drive each other in the unwanted pumping operation.
- FIG. 3 Another embodiment of the invention is shown in Fig. 3, which is advantageous enough for the full-load stop operation.
- the aim of this test sequence is that the heated shaft bearings of the hot turbocharger 1 are no longer conditioned, i. no heat dissipation takes place. This has the consequence that the loader body continues to heat up due to the heat still contained in the system and possibly damages the oil filling in the bearing.
- creep behavior of turbocharger bearings can be displayed under unfavorable operating conditions
- thermal damage mechanisms of the bearing can be anticipated or simulated and investigated (more precise VoI load-Abscha Itwholesome).
- the output 8a of the burner 3 is in turn divided into two lines 8b, 8c, the line 8b leading to the turbine side 1a of the turbocharger 1.
- Switching valves 9 in lines 8b, 8c can be used to close line 8b and open line 8c, which forms a switchable bypass around turbine side 1a of turbocharger 1 and opens into exhaust line 12 of turbine side 1a, preferably behind a possible pressure regulating valve 13.
- the installed loader 1 is set to perform the full-load stop operation stationary at the desired operating point and is completely warmed up. Then we the burner 3 spontaneously switched off, which means that through the turbine Ia no hot gas and through the compressor Ib no air mass flow is more promoted.
- the conditioning systems (water / lubricating oil) 6 are switched off.
- the burner 3 is driven with the fastest possible gradient to minimum power, the burner temperature is maintained as possible.
- the hot gas mass flow is reduced to the systemically possible minimum and bypassed in the bypass on the turbine Ia.
- This shutdown state is maintained for a time to be defined in the test run.
- the restart of the turbocharger 1 to be tested is carried out via a predefined routine, the previous setpoint operating point is approached again.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
- Supercharger (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112009001726T DE112009001726A5 (de) | 2008-07-24 | 2009-07-15 | Prüfanordnung und Prüfsystem für Turbolader |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ATGM409/2008 | 2008-07-24 | ||
AT0040908U AT10353U3 (de) | 2008-07-24 | 2008-07-24 | Prüfanordnung und prüfsystem für turbolader |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010010018A1 true WO2010010018A1 (de) | 2010-01-28 |
Family
ID=39944593
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2009/059042 WO2010010018A1 (de) | 2008-07-24 | 2009-07-15 | Prüfanordnung und prüfsystem für turbolader |
Country Status (3)
Country | Link |
---|---|
AT (1) | AT10353U3 (de) |
DE (1) | DE112009001726A5 (de) |
WO (1) | WO2010010018A1 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009041541C5 (de) * | 2009-09-15 | 2015-12-03 | Continental Automotive Gmbh | Verfahren und Vorrichtung zur Untersuchung des dynamischen Betriebsverhaltens eines Abgasturboladers |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0576697A1 (de) * | 1992-06-29 | 1994-01-05 | Abb Research Ltd. | Brennkammer einer Gasturbine |
US20070175219A1 (en) * | 2003-09-05 | 2007-08-02 | Michael Cornwell | Pilot combustor for stabilizing combustion in gas turbine engines |
-
2008
- 2008-07-24 AT AT0040908U patent/AT10353U3/de not_active IP Right Cessation
-
2009
- 2009-07-15 WO PCT/EP2009/059042 patent/WO2010010018A1/de active Application Filing
- 2009-07-15 DE DE112009001726T patent/DE112009001726A5/de not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0576697A1 (de) * | 1992-06-29 | 1994-01-05 | Abb Research Ltd. | Brennkammer einer Gasturbine |
US20070175219A1 (en) * | 2003-09-05 | 2007-08-02 | Michael Cornwell | Pilot combustor for stabilizing combustion in gas turbine engines |
Also Published As
Publication number | Publication date |
---|---|
AT10353U3 (de) | 2009-08-15 |
DE112009001726A5 (de) | 2011-06-01 |
AT10353U2 (de) | 2009-01-15 |
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