GB2101297A - Evaluating the quality of mixing in a combustion chamber - Google Patents
Evaluating the quality of mixing in a combustion chamber Download PDFInfo
- Publication number
- GB2101297A GB2101297A GB08119323A GB8119323A GB2101297A GB 2101297 A GB2101297 A GB 2101297A GB 08119323 A GB08119323 A GB 08119323A GB 8119323 A GB8119323 A GB 8119323A GB 2101297 A GB2101297 A GB 2101297A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fluid
- flow
- mixing
- quality
- fuel
- 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- Withdrawn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
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 62
- 239000012530 fluid Substances 0.000 claims abstract description 80
- 239000000446 fuel Substances 0.000 claims abstract description 65
- 239000003054 catalyst Substances 0.000 claims abstract description 43
- 230000005855 radiation Effects 0.000 claims abstract description 20
- 239000000203 mixture Substances 0.000 claims abstract description 18
- 238000009826 distribution Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 22
- 239000007789 gas Substances 0.000 description 9
- 239000001307 helium Substances 0.000 description 4
- 229910052734 helium Inorganic materials 0.000 description 4
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 4
- 238000011156 evaluation Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 229910052703 rhodium Inorganic materials 0.000 description 1
- 239000010948 rhodium Substances 0.000 description 1
- MHOVAHRLVXNVSD-UHFFFAOYSA-N rhodium atom Chemical compound [Rh] MHOVAHRLVXNVSD-UHFFFAOYSA-N 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0014—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation from gases, flames
-
- 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
- F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0014—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation from gases, flames
- G01J5/0018—Flames, plasma or welding
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J2005/0077—Imaging
Abstract
To evaluate the quality of mixing of fuel and air in a combustion chamber for use in a gas turbine engine, a first fluid (unheated air) which simulates the flow of combustion air is supplied to a mixing zone 40 in a combustion chamber 16 through an inlet 38 and a swirler assembly 24, and a second fluid (preheated air) which simulates the flow of fuel, is supplied to the mixing zone 40 through a fuel feed arm 34 and a fuel injector nozzle 32 and mixes with the first fluid. The mixture is then passed through a perforate body (honeycomb catalyst 36) and the temperature distribution at the downstream end, which corresponds to the quality of mixing of the fuel and air in the mixing zone 40 of the combustion chamber 16, is measured using an infrared radiation camera and a display unit. <IMAGE>
Description
SPECIFICATION
A method of evaluating the quality of mixing of fuel and air in a combustion chamber
The present invention relates to a method of evaluating the quality of mixing of fuel and air in a combustion chamber of a gas turbine engine.
In the last few years it has become more important to reduce the emissions of oxides or nitrogen (NOX), smoke, unburnt hydrocarbons (UHC) and carbon monoxide (CO) from gas turbine engines.
Onemethod used at present to achieve this result is the burning of very low fuel to air ratio (lean) mixtures in the combustion chambers of gas turbine engines. However, the lean mixture of fuel and air has low combustion efficiency and is susceptible to extinction at ground idle conditions.
To overcome these problems a catalyst has been employed to sustain complete combustion and prevent instability of combustion.
For the catalyst to operate efficiently the fuel and air must be mixed thoroughly prior to their entry into the catalyst, otherwise rich pockets of fuel could overheat and destroy the catalyst. It is therefore necessary to measure the mixing efficiency of the combustion chamber, without the use of a fuel and air mixture.
An existing method of analysing the mixing efficiency of fuel and air in a combustion chamber for use in a gas turbine engine comprises the use of air diluted helium to simulate fuel, and air. The air diluted helium is injected into the combustion chamber through a fuel burner and is mixed with the air flowing into the combustion chamber. A probe is installed downstream of the catalyst and is used to measure the concentration of helium at a plurality of points in a plane which is parallel to the downstream end of the catalyst. A plot of the helium concentration throughout the plane can be constructed and this gives a quantitative measure of the mixing efficiency of fuel and air in the combustion chamber.
The present invention seeks to provide a simpler and more economic method of analysing the quality of mixing of the fuel and air in the combustion chamber of a gas turbine engine.
Accordingly the present invention provides a method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid, the first and the second fluid being at different temperatures, the method comprising the steps of mixing the first and the second fluid together in a mixing zone and passing the mixture of the first and the second fluid through a perforate body, measuring the temperature distribution at the downstream surface of the perforate body using temperature measuring means, the temperature distributions at the downstream surface of the perforate body corresponding to the quality of mixing of the flow of the first fluid with the flow of the second fluid.
The first and second fluids may comprise two flows of air at different temperatures in which the hotter flow of air simulates a fuel flow and the cooler flow represents an air flow.
The perforate body may comprise a honeycomb catalyst and the temperature sensing means may comprise an infra-red camera and means capable of making a permanent record of the pictures produced by the camera.
The present invention will be more fully understood from the following description with reference to the accompanying drawings in which:
Figure 1 shows a cross-sectional view of a canannular combustion system for use in a gas turbine engine
Figure 2 shows a schematic arrangement of an apparatus used for evaluating the quality of mixing in a combustion chamber shown in Figure 1, and
Figure 3 shows an example of an instantaneous measurement of the temperature distribution at the downstream end of a honeycomb catalyst in the combustion chamber as shown on a display unit.
Figure 1 shows a cross-sectional view of a combustion system 10, which is of the canannular type and comprises inner and outer annular walls 12 and 14 respectively which contain a number of equi-spaced tubular combustion chambers 16, an annular air duct 1 8 being formed between the two walls 1 2, 14. Each combustion chamber 1 6 has a head 20 at its upstream end and the head 20 has an aperture 22. A swirler assembly 24 is positioned in the aperture 22 in the head 20 and the swirler assembly 24 comprises a number of swirl vanes 26 which extend between inner and outer cylindrical walls 28 and 30 respectively. A fuel injector 32 is fed with fuel by a fuel feed arm 34 and the fuel injector 32 is positioned coaxially inside the inner cylindrical wall 28 of the swirler assembly 24.A honeycomb catalyst 36 extends across the combustion chamber 1 6 downstream of the head 20. The combustion system 1 0 has an annular air inlet 38 at its upstream end, a mixing zone 40 positioned downstream of the head 20 and upstream of the honeycomb catalyst 36, and an exit 42 at the downstream end. The combustion chamber 1 6 has a plurality of holes 46 to permit air to flow from the annular air duct 18 into the mixing zone 40.
Figure 2 shows an arrangement of apparatus and for evaluating the quality of mixing of fuel and air in the mixing zone 40 of the combustion system 10. An infra-red radiation camera 100 is positioned downstream of a perforate body, in this case the honeycomb catalyst 36, and is arranged to receive radiation from as much of the surface area of the honeycomb catalyst 36 as possible.
The infra-red radiation camera 100 receives infrared radiation and sends electrical signals to a display unit 102, and a video magnetic tape recorder 104 may be used to keep permanent records of colour pictures shown on the display unit 102, or a colour photograph may be taken of the display shown on the display unit 1 02.A flow of a first fluid in this case unheated air is supplied into the mixing zone 40 of the combustion chamber 1 6 through the inlet 38, the swirler assembly 24 and the holes 46 to represent the normal airflow to the combustion chambers 1 6. A flow of a second fluid in this case preheated air is supplied into the mixing zone 40 of the combustion chamber 1 6 through the fuel feed arm 34 and the fuel injector 32 to simulate the normal fuel flow to the combustion chambers 1 6.
Figure 3 shows an example of the temperature distribution at the downstream end of the honeycomb catalyst as shown on the display unit
102 at a particular instant. At any instant an image 106 is produced on the display unit 102, and each image 106 comprises a number of bands of colour in this case 108, 110, 112, 114, 11 6.
With reference to Figure 1, air flows from a high pressure compressor (not shown) into the combustion chambers 1 6 through the inlet 38. A first portion of the air flows through the annular air duct 18 defined between the inner and outer
annular walls 12 and 14 respectively and is used to cool the walls of the combustion chambers 1 6
and to complete the dilution of fuel and air in the
mixing zones 40 and is supplied through the holes
46 in the combustion chamber 1 6.
The second portion of air flows through the
swirler assembly 24 positioned in the aperture 22
in the head 20 of the combustion chamber 16.
The air flow is given a swirling motion by the swirl
vanes 26 which extend between the inner and outer cylindrical walls 28 and 30 respectively of the swirler assembly 24, and the swirling air mixes with fuel injected into the mixing zone 40 of the combustion chamber 1 6 by the fuel injector 32.
The fuel injector 32 is supplied with fuel by the fuel feed arm 34 which is connected to a fuel supply (not shown).
The fuel and air mixture flows in a downstream direction into the honeycomb catalyst 36 where the fuel and air mixture burns, and the hot exhaust gases flow through the outlet 44 into a number of
turbines (not shown). Once the fuel and air mixture
is alight the mixture remains alight in all operating
conditions due to the presence of the honeycomb
catalyst 36. The honeycomb catalyst 36 also
promotes complete combustion of the fuel and air
mixtures.
If the mixture of fuel and air is not a uniform
mixture when it reaches the honeycomb catalyst 36 any rich pockets of fuel will be burnt in the porous catalyst 36. This burning of rich fuel pockets in the honeycomb catalyst 36 could lead to destruction of the honeycomb catalyst 36 in the locality of the rich fuel pocket. The destruction of the honeycomb catalyst 36 would be detrimental to the performance of the combustion chamber 16 and the gas turbine engine.
The quality of the mixing of the fuel and the air in the mixing zone 40 of the combustion chamber 1 6 can be analysed using the apparatus shown in
Figure 2. In operation, the combustion chamber 16 is supplied with a flow of a first fluid, in this case a flow of unheated air, which simulates the flow of air through the combustion chamber 1 6, and is supplied with a flow of a second fluid, in this case a flow of preheated air, which simulates the flow of fuel through the combustion chamber 1 6. The preheated air, is supplied through a fuel feed arm 34 to the fuel injector 32, and the fuel injector 32 injects the preheated air into the mixing zone 40.The unheated air flows through the inlet 38 and the swirler assembly 24 into the mixing zone 40 and mixes with the preheated air, and the mixture of preheated air and unheated air flows in a downstream direction and mixes with more of the unheated air entering the mixing zone 40 through the holes 46 in the combustion chamber 16. The preheated air and unheated air, flows through the honeycomb catalyst 36, and gives heat to the honeycomb catalyst 36. Each point on the surface of the honeycomb catalyst 36 emits radiation throughout the electromagnetic spectrum. It is known that the amount of energy emitted by any object at any particular wavelength increases with an increase of temperature, this makes it possible to detect points on the surface of the honeycomb catalyst 36 which have different temperatures.The majority of the energy
radiated by the surface of the honeycomb catalyst
36 is in the infra-red radiation band, this makes it
necessary to analyse the infra-red radiation
emitted by the surface of the honeycomb catalyst
36.
An infra-red radiation camera 100 is positioned
downstream of the honeycomb catalyst 36 and is
arranged to receive infra-red radiation from as
much of the surface of the honeycomb catalyst 36
as is possible. The infra-red radiation camera 100
receives infra-red radiation emitted from points on
the surface of the honeycomb catalyst 36 and
converts the infra-red radiation into a number of
electrical signals and sends the electrical signals
to the display unit 102. The display unit 102
produces instantaneous images from the electrical
signals, and each image shows the amount of
infra-red radiation emitted from each point on the
surface of the honeycomb catalyst 36 at any
instant in time.
The image corresponds to the temperature
distribution of the surface of the honeycomb
catalyst 36, and therefore to the quality of the
mixing of the preheated air, and unheated air, in
the mixing zone 40.
As an example, the first fluid, unheated air at a
temperature of 22"C and having a pressure of 1
atmosphere was supplied to the combustion
chamber 1 6 at a flow rate of 0.43 kg/sec, and the
second fluid, preheated air at a temperature of
650C and having a pressure of 1 atmosphere was
supplied to the combustion chamber 1 6. Any
piping used to convey the preheated air to the fuel
burner 32 was insulated in order to retain a
reasonable temperature difference between the
first and the second fluid. The greater the
temperature difference between the first fluid and
the second fluid, the better the resolution in the
resulting image on the display unit 102.
An example of an infra-red radiation camera
100 and a display unit 102 used for the anaiysis is
a system sold under the trade name AGA
THERMOVISION SYSTEM 680 which comprises an infra-red camera unit model 680 and display unit model 102B.
A permanent record of the temperature distribution of the surface of the honeycomb catalyst 36 can be made on a magnetic video tape using a magnetic video tape recorder 104 connected to the display unit 102, or a number of instantaneous records can be made on colour photographic film using a colour photographic camera.
The quality of the mixing of the second fluid and the first fluid in the mixing zone 40 corresponds to the quality of mixing of the fuel and air in the mixing zone 40 of the combustion chamber 16.
The image 106 produced on the display unit 102 comprises a number of coloured bands 108, 110, 112, 114 and 116 respectively. Each band is a different colour or shade and corresponds to a number of points or a region on the surface of the honeycomb catalyst 40 which are at the same temperature i.e. they are isothermal bands. In this particular case, band 11 6 corresponds to a relatively high temperature and hence a relatively rich mixture of fuel and air, band 108 to a relatively cool temperature and hence to a relatively lean mixture of fuel and air and bands 110, 112 and 114 correspond to regions having temperatures inbetween.
The honeycomb catalyst 36 comprises a honeycomb structure upon which a catalyst such as platinum or rhodium is deposited. The
honeycomb structure used has a large number of
cells, for example 31 or 62 cells per cm2, this large
number of cells per unit area allows the preheated
and unheated air mixture to flow freely through
the catalyst 36, to give a true evaluation of the
quality of mixing of the preheated and unheated
air. Large numbers of perforations in the perforate
body are necessary to give a true evaluation.
The first and second fluid need not be air, they
may be varied to correspond to the density of fuel to be simulated.
Other types of fuel injectors may be used in the
combustion chambers, for example, the fuel and
air injector described in our co-pending UK patent
application which comprises two conjoined plates
having a number of apertures therethrough for the flow of air and an internal arrangement of
passages for supplying fuel to the apertures.
The invention has been described with
reference to a can-annular combustion chamber, it
may also be applied to a tubular combustion
chamber or an annular combustion chamber.
The method could equally weil be applied to a
combustion chamber burning more than one fuel
e.g. oil and gas in which case three fluids would be
required all having different temperatures.
The method could also be applied to other
systems where two fluids are mixed together, and
where an evaluation of the quality of mixing of the
fluids is required.
The method and apparatus described gives a
qualitative measure of the mixing of the fuel and
air in the combustion chamber, it does not give a quantitative measure of the mixing.
Claims (11)
1. A method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid, the first and second fluid being at different temperatures, the method comprising the steps of:
mixing the first and the second fluid together in a mixing zone and passing the mixture of the first and the second fluid through a perforate body,
measuring the temperature distribution at the downstream surface of the perforate body using temperature measuring means,
the temperature distribution at the downstream surface of the perforate body corresponding to the quality of mixing of the flow of the first fluid with the flow of the second fluid.
2. A method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid as claimed in claim 1 , the first and the second fluid being mixed together in the mixing zone of a combustion chamber for use in a gas turbine engine, the perforate body being a honeycomb catalyst positioned in and arranged for use in the combustion chamber, the flow of the first fluid simulating the flow of combustion air and the flow of the second fluid simulating the flow of fuel in the combustion chamber, the quality of mixing of the flow of the first fluid with the flow of the second fluid corresponding to the quality of mixing of the flow of fuel with the flow of combustion air in the combustion chamber.
3. A method of evaluating the quality of mixing
of a flow of a first fluid with a flow of a second fluid as claimed in either claim 1 or claim 2, in which the first fluid and the second fluid is air, the temperature of the second fluid being greater than that of the first fluid.
4. A method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid as claimed in claim 3 in which the first fluid is
unheated air and the second fluid is preheated air.
5. A method of evaluating the quality of mixing
of a flow of a first fluid with a flow of a second fluid as claimed in any of claims 1 to 4 in which the temperature measuring means comprises an
infra-red radiation camera and a display unit.
6. A method of evaluating the quality of mixing
of a flow of a first fluid with a flow of a second fluid as claimed in claim 5 in which a magnetic
video recorder is used to record a number of images
produced on the display unit on a magnetic video tape.
7. A method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid as claimed in claim 5 in which a colour photographic camera is used to record an image produced on the display unit on a colour photographic film.
8. Apparatus for use in a method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid, the first and second fluid being at different temperatures, the apparatus comprising a combustion chamber for use in a gas turbine engine, a supply of a first fluid, a supply of a second fluid and a temperature measuring means, the combustion chamber has a mixing zone downstream of a head the combustion chamber has at least one aperture for supplying the first fluid into the mixing zone and means to supply the second fluid into the mixing zone, the mixture of the first and second fluid passes through the honeycomb catalyst, the temperature measuring means is positioned downstream of the honeycomb catalyst and comprises an infra-red radiation camera and a display unit, the infra-red radiation camera is arranged to receive radiation from as much of the surface of the honeycomb catalyst as possible, the display unit produces images of the temperature distribution at the downstream surface of the honeycomb catalyst from electrical signals sent by the infra-red radiation camera the temperature distribution corresponds to the quality of mixing of the flow of the first fluid with the flow of the second fluid.
9. Apparatus for use in a method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid as claimed in claim 8, in which a fuel injector is positioned coaxially in an aperture in the head, and a swirler assembly is positioned coaxially in the aperture and around the fuel injector, the first fluid is supplied through the swirler assembly into the mixing zone and the second fluid is supplied through a fuel feed arm and the fuel injector into the mixing zone.
10. Apparatus for use in a method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid as claimed in claim 8, in which a fuel and air injector extends across the combustion chamber downstream of the head, the fuel and air injector comprises two conjoined plates having a number of apertures therethrough for the through flow of the first fluid into the mixing zone and an internal arrangement of passages for supplying the second fluid to the apertures in the fuel and air injector, the second fluid flows with the first fluid through the apertures into the mixing zone.
11. A method of evaluating the quality of mixing of a flow of a first fluid with a flow of second fluid substantially as herein described and with reference to the accompanying drawings.
-12. Apparatus for use in a method of evaluating the quality of mixing of a flow of a first fluid with a flow of a second fluid substantially as herein described and with reference to the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08119323A GB2101297A (en) | 1981-06-23 | 1981-06-23 | Evaluating the quality of mixing in a combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08119323A GB2101297A (en) | 1981-06-23 | 1981-06-23 | Evaluating the quality of mixing in a combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2101297A true GB2101297A (en) | 1983-01-12 |
Family
ID=10522744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08119323A Withdrawn GB2101297A (en) | 1981-06-23 | 1981-06-23 | Evaluating the quality of mixing in a combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2101297A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0320746A1 (en) * | 1987-12-17 | 1989-06-21 | Bayerische Motoren Werke Aktiengesellschaft, Patentabteilung AJ-3 | Gas turbine plant |
| PL423430A1 (en) * | 2017-11-14 | 2019-05-20 | Politechnika Poznanska | System and method for initial assessment of technical condition of electromagnetic injectors |
| CN110793777A (en) * | 2019-10-23 | 2020-02-14 | 清华大学 | Testing arrangement of effect is preheated in simulation diesel engine intake duct environment air admission |
-
1981
- 1981-06-23 GB GB08119323A patent/GB2101297A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0320746A1 (en) * | 1987-12-17 | 1989-06-21 | Bayerische Motoren Werke Aktiengesellschaft, Patentabteilung AJ-3 | Gas turbine plant |
| PL423430A1 (en) * | 2017-11-14 | 2019-05-20 | Politechnika Poznanska | System and method for initial assessment of technical condition of electromagnetic injectors |
| CN110793777A (en) * | 2019-10-23 | 2020-02-14 | 清华大学 | Testing arrangement of effect is preheated in simulation diesel engine intake duct environment air admission |
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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) |