WO2012039611A1 - Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine - Google Patents

Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine Download PDF

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Publication number
WO2012039611A1
WO2012039611A1 PCT/NL2011/050636 NL2011050636W WO2012039611A1 WO 2012039611 A1 WO2012039611 A1 WO 2012039611A1 NL 2011050636 W NL2011050636 W NL 2011050636W WO 2012039611 A1 WO2012039611 A1 WO 2012039611A1
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WO
WIPO (PCT)
Prior art keywords
air
fuel
stabilization device
inlet
flame stabilization
Prior art date
Application number
PCT/NL2011/050636
Other languages
French (fr)
Inventor
Savad Shakariyants
Original Assignee
Micro Turbine Technology Bv
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Micro Turbine Technology Bv filed Critical Micro Turbine Technology Bv
Priority to EP11773910.2A priority Critical patent/EP2619507B1/en
Publication of WO2012039611A1 publication Critical patent/WO2012039611A1/en
Priority to US13/848,276 priority patent/US20130213050A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/03001—Miniaturized combustion devices using fluid fuels

Definitions

  • the invention relates to a combustor comprising:
  • a liner being within said casing and having a further cylindrical wall at a distance from the casing wall, an outlet opening on one end and an inlet opening on the other end;
  • a combustor is known from US-A-2010/0126174.
  • This combustor includes: a flame tube having, in the direction of the flow, a mixing zone for mixing the fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a post-primary combustion zone. At least one opening is being provided in the area of the mixing zone and in the area of the post-primary combustion zone in order to conduct compressed air into the flame tube.
  • the supplied compressed air is used to cool the flame tube and passes, via the openings in the area of the mixing zone and in the area of the post-primary combustion zone, partly into the mixing zone and into the post-primary combustion zone.
  • combustors are known from US2009019855 Al, US2010000218A1, US2010071377 Al, WO 0075573A1. These combustors have main burners that require assistance from pilot burners to ensure stable and complete combustion, as well as reliable light-off at all operating conditions.
  • a suitable combustion chamber for a recuperated micro gas turbine is challenged by the following factors:
  • the combustor according to the invention is characterized in that the relative position of the fuel injector and flame stabilization device in the burner is such that the burner stages first complete combustion of the fuel in the air through the air passages of the flame stabilization device where fuel is injected and then mixing with the air through the neighboring passages as such that NOx can never increase above single-digit ppm.
  • the fuel injector position relative to the flame stabilization device is chosen as to:
  • the burner according to the invention stages first combustion of the fuel in the given part of the air and then mixing with the remaining air. In particualr, combustion is complete and mixing occurs as such that NOx can never increase above single-digit ppm.
  • the fuel injector is present in the middle of the liner inlet opening
  • the flame stabilization device is present in the inlet opening around the fuel injector and extends directly from the fuel injector to the boundary wall of the inlet opening.
  • An embodiment of the combustor according to the invention is characterized in that the flame stabilization device comprises two concentrically cylindrical rings and vanes extending in the radial direction from one ring to the other ring and being at an angle with the axial direction, wherein an air passage is present between two neighboring vanes of the flame stabilization device, and the geometry of the said rings, vanes and air passages result in a pressure loss over the flame stabilization device less than 1,5%.
  • This flame stabilization device has a swirl strength and air passage cross section as such that the pressure loss over the device is less than 1,5%.
  • the pressure loss is dependent, among other parameters, on the geometry of the air passages, the flow rate and the flow density.
  • the geometry of the air passages determines the swirl strength. Contrary to the common knowledge and experience, it has been established and confirmed experimentally that stable burning can be maintained in the combustor according to the invention even when the pressure loss is between 1% and 1.5%.
  • the flame stabilization device and the fuel injector form together with the liner inlet hardware a single burner, which guarantees both stable and complete combustion and low NOx at all operating regimes - steady state and transient.
  • the same single burner guarantees reliable light-off at all conditions encountered in operation. This single burner is not assisted by any other burner.
  • a further embodiment of the combustor according to the invention is characterized in that the number of vanes in the flame stabilization device is such that only part of the air through the flame stabilization device can mix with fuel.
  • An air passage is present between each two neighboring vanes of the flame stabilization device.
  • the fuel injector is provided with injection holes that inject fuel into a number of the air passages as such that the fuel is injected only in one passage from each set of two neighboring passages.
  • Such fuel injection allows limited fuel-air mixing, where fuel is mixed with only part of the air. Due to this, the fuel-air mixture formed in the passages where fuel is injected is optimal for high stability of burning.
  • high NOx levels can also form in the burned gases. Formation of high NOx levels is though prevented by quick mixing of these burned gases with the air that passes through the neighboring passages.
  • the invention further relates to a recuperated micro gas turbine comprising:
  • an air compressor having an air inlet and an air outlet
  • recuperator having an inlet and outlet for gases to be preheated and an inlet and outlet for hot gasses to be cooled, wherein the inlet for gases to be heated is connected to the outlet of the air compressor;
  • a combustor according to the invention described above having an air inlet and an outlet for burned gasses, wherein the inlet is being connected to the outlet of gasses heated in the recuperator;
  • a fuel delivery device compressor in case of gaseous fuels and a pump in case of liquid fuels connected to the combustor;
  • a turbine having an inlet connected to the outlet of the combustor and an outlet connected to the inlet of the gasses to be cooled in the recuperator.
  • the invention further relates to a method for operating a gas turbine according to the invention, which is characterized in that the temperature of gases coming from the turbine is kept constant at the recuperator inlet.
  • the flame stabilization is improved at part-load operating points where the shaft power is less than at the base-load operating point. This improvement is realized by limiting reduction in the fuel-air ratio associated with modulation of the gas turbine from the base load to part load.
  • micro gas turbines are environmentally and cost effective for distributed power and/or heat and/or cooling generation in households, hotels, farms, restaurants, offices, etc., as well as for vehicular applications.
  • the recuperated micro gas turbine according to the invention can be for: Electrical power generation systems.
  • FIG 1 shows an embodiment of the recuperated micro gas turbine according to the invention
  • FIG. 2 shows the combustor of the recuperated micro gas turbine
  • Figure 3 shows the flame stabilization device of the combustor
  • Figure 4 shows the fuel injector of the combustor
  • Figure 5 shows a burner of the combustor in cross section composed of the flame stabilization device, fuel injector and liner inlet/head hardware.
  • the recuperated micro gas turbine 1 comprises an air compressor 3, a combustor 5, a fuel compressor 7 (for gaseous fuels) or pump (for liquid fuels), a recuperator 9 and a turbine 11.
  • the turbine drives the air compressor via a shaft 13.
  • the excess mechanical power produced by the turbine is converted into electrical power in a generator 15.
  • the generator is either coupled to the turbine- compressor shaft or has its rotor mounted on the turbine-compressor shaft.
  • the gases can be directed either to a gas-to- water heat exchanger 17 or other equipment for either heat or cooling production.
  • the combustor 5 typically receives air 19 compressed in the gas turbine air compressor and preheated in the recuperator.
  • Fuel 21 to the combustor is delivered by either fuel compressor (for gaseous fuels) or fuel pump (for liquid fuels).
  • the geometric envelope of the combustor is delimited by the casing 23.
  • the air flow is diffused in the casing inlet diffuser 25 and dumped into the casing.
  • a liner 27 (or flame tube) is mounted inside the casing.
  • the inlet or head 28 of the liner is equipped with a flame stabilization device 29.
  • the liner is also equipped with a system of air admission holes 31 and cooling arrangements. Combustion is staged inside the liner.
  • the air flow is divided between the flame stabilization device 29, cooling arrangement and air admission holes 31.
  • the fuel injector 33 is usually located in the vicinity of the flame stabilization device 29.
  • the air flow through the flame stabilization device is usually the combustion air. Fuel is injected and mixed with this air.
  • the flame stabilization device 29, fuel injector 33 and liner inlet/head hardware 28 are commonly referred to as burner.
  • the flame 35 is stabilized downstream the fuel stabilization device 29.
  • the air through the air admission holes 31 is mixed with the products of combustion. This air is called dilution air. Cooling air is gradually mixed with the gases. Diluted gases 37 are directed into the turbine at the combustor outlet 39.
  • the flame stabilization device 29 is shown.
  • the flame stabilization device comprises two concentrically cylindrical rings 41 and 43 and a number of vanes 45 extending in radial direction from one ring to the other ring and being at an angle with the axial direction 47. Air passages 49 are present between the vanes.
  • the fuel injector 33 of the combustor is shown.
  • the fuel injector comprises a number of injection holes 51 over the circumference of the injector such that fuel is only injected into half the number of air passages in the flame stabilization device, whereby fuel is injected alternately in one passage and no fuel is injected in the next passage.
  • FIG 5 a cross section of the burner composed of the flame stabilization device, fuel injector and liner head hardware is shown.
  • the position of the fuel injector 33 relative to the flame stabilization device 29 is chosen for optimal limited fuel-air mixing. It allows the burner to stage first complete combustion of the fuel in the given part of the air and then mixing with the remaining air as such that NOx can never increase above single-digit ppm.

Abstract

According to the invention, a recuperated micro gas turbine combustor has a casing (23), liner (27), fuel injector (33) and a flame stabilization device (29). This flame stabilization device is characterized by a swirl strength and air passage geometry as such that the pressure loss over the device is less than 1,5%. The flame stabilization device and the fuel injector form together with the liner inlet/head hardware a single burner. The position of the fuel injector with respect to the flame stabilization device is optimized for limited fuel mixing with only part of the air through the flame stabilization device. The burner first stages combustion of the mixed fuel and then mixing with the remaining air. Particularly, combustion is complete and mixing occurs as such that NOx can never increase above single-digit ppm.

Description

Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine
DESCRIPTION:
Technical filed of the invention
The invention relates to a combustor comprising:
- a casing having a cylindrical wall provided with an opening for compressed air;
a liner being within said casing and having a further cylindrical wall at a distance from the casing wall, an outlet opening on one end and an inlet opening on the other end; and
- a single burner comprising a fuel injector, flame stabilization device and the hardware of the liner inlet (liner head).
Background of the invention A combustor is known from US-A-2010/0126174. This combustor includes: a flame tube having, in the direction of the flow, a mixing zone for mixing the fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a post-primary combustion zone. At least one opening is being provided in the area of the mixing zone and in the area of the post-primary combustion zone in order to conduct compressed air into the flame tube. The supplied compressed air is used to cool the flame tube and passes, via the openings in the area of the mixing zone and in the area of the post-primary combustion zone, partly into the mixing zone and into the post-primary combustion zone.
Other combustors are known from US2009019855 Al, US2010000218A1, US2010071377 Al, WO 0075573A1. These combustors have main burners that require assistance from pilot burners to ensure stable and complete combustion, as well as reliable light-off at all operating conditions.
Yet another combustor is known from US2002148232A1, which has multiple burners. None of the individual burners is capable to ensure adequate combustion performance at all operating conditions. Different burners, also in different combinations, have to operate at different operating conditions.
A suitable combustion chamber for a recuperated micro gas turbine is challenged by the following factors:
- Combustor pressure loss has to remain low. With the low compressor pressure ratio of recuperated micro turbines, pressure loss substantially penalizes the power output and efficiency. Typically, the relative burner pressure loss cannot exceed 2%.
Emission of undesirable chemicals has to be low, namely UHC, CO and NOx. CO and UHC can be effectively oxidized if flow temperature is maintained above 1500 C (-1800 K). At these temperatures, NOx formation accelerates. However, NOx has to be maintained at single-digit ppm. Stable and complete combustion has to be maintained along with low NOx at all operating points between base load and part load. At the same time, stable, complete and low NOx operation has to be guaranteed at light- off and during transients with both cold and hot recuperator.
Summary of the invention It is an object of the present invention to provide a combustor which is optimized for:
Operation in a recuperated micro gas turbine;
Low pressure loss;
Complete combustion and therefore low emission of CO and UHC; - Low emission of NOx;
Stable and low-emission operation at base load (with hot recuperator);
Stable and low-emission operation at part load;
Reliable light-off at cold conditions (with cold recuperator);
Reliable light-off at other conditions;
- Stable and low-emission operation during transients;
Stable and low-emission operation at other conditions; and
Low cost.
To this end, the combustor according to the invention is characterized in that the relative position of the fuel injector and flame stabilization device in the burner is such that the burner stages first complete combustion of the fuel in the air through the air passages of the flame stabilization device where fuel is injected and then mixing with the air through the neighboring passages as such that NOx can never increase above single-digit ppm.
The fuel injector position relative to the flame stabilization device is chosen as to:
One hand, give the necessary residence time for the fuel to combust in the air through the air passages where fuel is injected; and
On the other hand, mix in the air through the neighboring passages before high NOx levels have been formed.
In the other words, the burner according to the invention stages first combustion of the fuel in the given part of the air and then mixing with the remaining air. In particualr, combustion is complete and mixing occurs as such that NOx can never increase above single-digit ppm.
Preferably the fuel injector is present in the middle of the liner inlet opening, and the flame stabilization device is present in the inlet opening around the fuel injector and extends directly from the fuel injector to the boundary wall of the inlet opening.
An embodiment of the combustor according to the invention is characterized in that the flame stabilization device comprises two concentrically cylindrical rings and vanes extending in the radial direction from one ring to the other ring and being at an angle with the axial direction, wherein an air passage is present between two neighboring vanes of the flame stabilization device, and the geometry of the said rings, vanes and air passages result in a pressure loss over the flame stabilization device less than 1,5%.
This flame stabilization device has a swirl strength and air passage cross section as such that the pressure loss over the device is less than 1,5%. The pressure loss is dependent, among other parameters, on the geometry of the air passages, the flow rate and the flow density. The geometry of the air passages determines the swirl strength. Contrary to the common knowledge and experience, it has been established and confirmed experimentally that stable burning can be maintained in the combustor according to the invention even when the pressure loss is between 1% and 1.5%.
The flame stabilization device and the fuel injector form together with the liner inlet hardware a single burner, which guarantees both stable and complete combustion and low NOx at all operating regimes - steady state and transient. The same single burner guarantees reliable light-off at all conditions encountered in operation. This single burner is not assisted by any other burner.
A further embodiment of the combustor according to the invention is characterized in that the number of vanes in the flame stabilization device is such that only part of the air through the flame stabilization device can mix with fuel.
An air passage is present between each two neighboring vanes of the flame stabilization device. The fuel injector is provided with injection holes that inject fuel into a number of the air passages as such that the fuel is injected only in one passage from each set of two neighboring passages. Such fuel injection allows limited fuel-air mixing, where fuel is mixed with only part of the air. Due to this, the fuel-air mixture formed in the passages where fuel is injected is optimal for high stability of burning. However, high NOx levels can also form in the burned gases. Formation of high NOx levels is though prevented by quick mixing of these burned gases with the air that passes through the neighboring passages.
The invention further relates to a recuperated micro gas turbine comprising:
an air compressor having an air inlet and an air outlet;
a recuperator having an inlet and outlet for gases to be preheated and an inlet and outlet for hot gasses to be cooled, wherein the inlet for gases to be heated is connected to the outlet of the air compressor;
a combustor according to the invention described above having an air inlet and an outlet for burned gasses, wherein the inlet is being connected to the outlet of gasses heated in the recuperator;
a fuel delivery device (compressor in case of gaseous fuels and a pump in case of liquid fuels) connected to the combustor; and
a turbine having an inlet connected to the outlet of the combustor and an outlet connected to the inlet of the gasses to be cooled in the recuperator.
The invention further relates to a method for operating a gas turbine according to the invention, which is characterized in that the temperature of gases coming from the turbine is kept constant at the recuperator inlet. By this, the flame stabilization is improved at part-load operating points where the shaft power is less than at the base-load operating point. This improvement is realized by limiting reduction in the fuel-air ratio associated with modulation of the gas turbine from the base load to part load.
There is a great potential for employing micro gas turbines in an electrical power range from 1 kWe to 5 kWe. In particular, micro gas turbines are environmentally and cost effective for distributed power and/or heat and/or cooling generation in households, hotels, farms, restaurants, offices, etc., as well as for vehicular applications.
The recuperated micro gas turbine according to the invention can be for: Electrical power generation systems.
- The use in combined heat and electrical power systems, wherein the gas turbine drives an electrical generator to produce electrical power, and the heat in the gas turbine exhaust is - optionally - utilized for heating, such as space heating, water heating, etc. The heat can be also utilized to produce cooling. The use in various heat and power systems in combination with other energy conversion devices, such as fuel cells, Rankine engines, etc.
The use in auxiliary systems in automotive, maritime and other vehicles.
Brief description of the drawings The invention will be further elucidated below on the basis of drawings.
These drawings show an embodiment of the combustor, combustor burner and recuperated micro gas turbine according to the invention. In the drawings:
Figure 1 shows an embodiment of the recuperated micro gas turbine according to the invention;
- Figure 2 shows the combustor of the recuperated micro gas turbine;
Figure 3 shows the flame stabilization device of the combustor;
Figure 4 shows the fuel injector of the combustor; and
Figure 5 shows a burner of the combustor in cross section composed of the flame stabilization device, fuel injector and liner inlet/head hardware.
Detailed description of the drawings In Figure 1, an embodiment of the recuperated micro gas turbine is shown according to the invention. The recuperated micro gas turbine 1 comprises an air compressor 3, a combustor 5, a fuel compressor 7 (for gaseous fuels) or pump (for liquid fuels), a recuperator 9 and a turbine 11. The turbine drives the air compressor via a shaft 13. The excess mechanical power produced by the turbine is converted into electrical power in a generator 15. The generator is either coupled to the turbine- compressor shaft or has its rotor mounted on the turbine-compressor shaft. After recuperator, the gases can be directed either to a gas-to- water heat exchanger 17 or other equipment for either heat or cooling production.
The combustor 5, see Figure 2, typically receives air 19 compressed in the gas turbine air compressor and preheated in the recuperator. Fuel 21 to the combustor is delivered by either fuel compressor (for gaseous fuels) or fuel pump (for liquid fuels). The geometric envelope of the combustor is delimited by the casing 23. The air flow is diffused in the casing inlet diffuser 25 and dumped into the casing. Inside the casing, a liner 27 (or flame tube) is mounted. The inlet or head 28 of the liner is equipped with a flame stabilization device 29. The liner is also equipped with a system of air admission holes 31 and cooling arrangements. Combustion is staged inside the liner. The air flow is divided between the flame stabilization device 29, cooling arrangement and air admission holes 31. The fuel injector 33 is usually located in the vicinity of the flame stabilization device 29. The air flow through the flame stabilization device is usually the combustion air. Fuel is injected and mixed with this air. The flame stabilization device 29, fuel injector 33 and liner inlet/head hardware 28 are commonly referred to as burner. The flame 35 is stabilized downstream the fuel stabilization device 29. After combustion has been either fully or essentially completed, the air through the air admission holes 31 is mixed with the products of combustion. This air is called dilution air. Cooling air is gradually mixed with the gases. Diluted gases 37 are directed into the turbine at the combustor outlet 39.
In Figure 3, the flame stabilization device 29 is shown. The flame stabilization device comprises two concentrically cylindrical rings 41 and 43 and a number of vanes 45 extending in radial direction from one ring to the other ring and being at an angle with the axial direction 47. Air passages 49 are present between the vanes.
In Figure 4, the fuel injector 33 of the combustor is shown. The fuel injector comprises a number of injection holes 51 over the circumference of the injector such that fuel is only injected into half the number of air passages in the flame stabilization device, whereby fuel is injected alternately in one passage and no fuel is injected in the next passage.
In Figure 5, a cross section of the burner composed of the flame stabilization device, fuel injector and liner head hardware is shown. The position of the fuel injector 33 relative to the flame stabilization device 29 is chosen for optimal limited fuel-air mixing. It allows the burner to stage first complete combustion of the fuel in the given part of the air and then mixing with the remaining air as such that NOx can never increase above single-digit ppm.
Although the present invention is elucidated above on the basis of the given drawings, it should be noted that this invention is not limited whatsoever to the embodiments shown in the drawings. The invention also extends to all embodiments deviating from the embodiments shown in the drawings within the context defined by the claims.

Claims

CLAIMS:
1. Combustor comprising:
a casing having a cylindrical wall provided with an opening for compressed air;
- a liner being within said casing and having a further cylindrical wall at a distance from the casing wall, an outlet opening on one end and an inlet opening on the other end; and
one single burner comprising a fuel injector to inject fuel into the liner and a flame stabilization device comprising air passages,
characterized in that the relative position of the fuel injector and flame stabilization device in the burner is such that the burner stages first complete combustion of the fuel in the air through the air passages of the flame stabilization device where fuel is injected and then mixing with the air through the neighboring passages as such that NOx can never increase above single-digit ppm.
2. Combustor according to claim 1, characterized in that the fuel injector is present in the middle of the liner inlet opening, and the flame stabilization device is present in the inlet opening around the fuel injector and extends directly from the fuel injector to the boundary wall of the inlet opening.
3. Combustor according to claim 2, characterized in that the flame stabilization device comprises two concentrically cylindrical rings and vanes extending in the radial direction from one ring to the other ring and being at an angle with the axial direction, wherein an air passage is present between two neighboring vanes of the flame stabilization device, and the geometry of the said rings, vanes and air passages result in a pressure loss over the flame stabilization device less than 1,5%.
4. Combustor according to claim 3, characterized in that the fuel injector is provided with injection holes which during operation inject fuel into the airflow through a part of the total number of the air passages.
5. Combustor according to claim 4, characterized in that the injection holes are arranged over the circumference of the fuel injector such that fuel is only injected into half the number of air passages in the flame stabilization device.
6. Recuperated micro gas turbine comprising:
an air compressor having an air inlet and an air outlet;
a recuperator having an inlet and outlet for gases to be preheated and an inlet and outlet for hot gasses to be cooled, wherein the inlet for gases to be heated is connected to the outlet of the air compressor;
a combustor according to one of the previous claims having an air inlet and an outlet for burned gasses, wherein the inlet is connected to the outlet of gasses heated in the recuperator,
a fuel delivery device connected to the combustor, and
a turbine having an inlet connected to the outlet of the combustor and an outlet connected to the inlet of the gasses to be cooled of the recuperator.
7. Combustor according to one of the previous claims characterized in having the burner according to one of the previous claims 1 to 5, which is the single and non- assisted burner for complete combustion, single-digit ppm NOx and reliable light-off under all operating conditions in a recuperated micro gas turbine according to claim 6.
8. Method for operating a recuperated gas turbine according to claim 6, characterized in that the temperature of gases coming from the turbine is kept constant at the recuperator inlet.
PCT/NL2011/050636 2010-09-21 2011-09-20 Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine WO2012039611A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11773910.2A EP2619507B1 (en) 2010-09-21 2011-09-20 Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine
US13/848,276 US20130213050A1 (en) 2010-09-21 2013-03-21 Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL2005381 2010-09-21
NL2005381A NL2005381C2 (en) 2010-09-21 2010-09-21 Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.

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US13/848,276 Continuation US20130213050A1 (en) 2010-09-21 2013-03-21 Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine

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WO2012039611A1 true WO2012039611A1 (en) 2012-03-29

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EP (1) EP2619507B1 (en)
NL (1) NL2005381C2 (en)
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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014134182A3 (en) * 2013-02-26 2014-11-06 Electric Jet, Llc Micro gas turbine engine for powering a generator
FR3041742A1 (en) * 2015-09-30 2017-03-31 Ifp Energies Now COMBUSTION CHAMBER FOR A TURBINE, IN PARTICULAR A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, ESPECIALLY ELECTRICAL ENERGY.
WO2017157631A1 (en) 2016-03-18 2017-09-21 IFP Energies Nouvelles Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy
WO2018041455A1 (en) 2016-08-29 2018-03-08 IFP Energies Nouvelles Combustion chamber with a hot compressed air deflector, in particular for a turbine intended for producing energy, in particular electrical energy
WO2018041454A1 (en) 2016-08-29 2018-03-08 IFP Energies Nouvelles Modular turbine, in particular turbine with heat exchanger for producing energy, in particular electrical energy
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106247403B (en) * 2016-08-02 2019-08-02 北京航空航天大学 A kind of miniature gas turbine combustion chamber of double-wall structure
USD910717S1 (en) 2018-07-31 2021-02-16 Hotstart, Inc. Rotary atomizer
US20200041130A1 (en) * 2018-07-31 2020-02-06 Hotstart, Inc. Combustor Systems
US11824424B2 (en) 2021-09-10 2023-11-21 Hamilton Sundstrand Corporation Combined integrated waste heat recovery and inlet pressure boost system

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE23149E (en) * 1949-09-20 Combustion burner
US5163287A (en) * 1989-12-22 1992-11-17 Sundstrand Corporation Stored energy combustor with fuel injector containing igniter means for accommodating thermal expansion
EP0638768A2 (en) * 1993-08-09 1995-02-15 United Technologies Corporation Fuel nozzle with non-axisymmetrical secondary spray
US5477685A (en) * 1993-11-12 1995-12-26 The Regents Of The University Of California Lean burn injector for gas turbine combustor
EP0933594A1 (en) * 1998-01-28 1999-08-04 Institut Francais Du Petrole Gas turbine combustion chamber for liquid fuel
WO2000075573A1 (en) 1999-06-09 2000-12-14 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
WO2001018371A1 (en) * 1999-09-07 2001-03-15 Geza Vermes Ambient pressure gas turbine system
US20020148232A1 (en) 2000-02-24 2002-10-17 Willis Jeffrey W. Gas turbine engine having a multi-stage multi-plane combustion system
US20040098965A1 (en) * 2002-11-27 2004-05-27 Dettmer Gregory Brian Microturbine direct fired absorption chiller
US20090019855A1 (en) 2006-05-04 2009-01-22 General Electric Company Low emissions gas turbine combustor
US20100000218A1 (en) 2003-06-19 2010-01-07 Hitachi, Ltd. Gas turbine combustor and fuel supply method for same
US20100071377A1 (en) 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine
US20100126174A1 (en) 2006-09-07 2010-05-27 Rainer Brinkmann Gas turbine combustion chamber

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4724483Y1 (en) * 1970-12-22 1972-08-02
US3853273A (en) * 1973-10-01 1974-12-10 Gen Electric Axial swirler central injection carburetor
US4274253A (en) * 1977-12-22 1981-06-23 The Garrett Corporation Control for turbine and recuperator inlet temperatures
FR2706985B1 (en) * 1993-06-22 1995-08-25 Pillard Ent Gle Chauffage Indl
US6907724B2 (en) * 2002-09-13 2005-06-21 The Boeing Company Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance
JP4486549B2 (en) * 2005-06-06 2010-06-23 三菱重工業株式会社 Gas turbine combustor
EP2085695A1 (en) * 2008-01-29 2009-08-05 Siemens Aktiengesellschaft Fuel nozzle with swirl duct and method for manufacturing a fuel nozzle

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE23149E (en) * 1949-09-20 Combustion burner
US5163287A (en) * 1989-12-22 1992-11-17 Sundstrand Corporation Stored energy combustor with fuel injector containing igniter means for accommodating thermal expansion
EP0638768A2 (en) * 1993-08-09 1995-02-15 United Technologies Corporation Fuel nozzle with non-axisymmetrical secondary spray
US5477685A (en) * 1993-11-12 1995-12-26 The Regents Of The University Of California Lean burn injector for gas turbine combustor
EP0933594A1 (en) * 1998-01-28 1999-08-04 Institut Francais Du Petrole Gas turbine combustion chamber for liquid fuel
WO2000075573A1 (en) 1999-06-09 2000-12-14 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
WO2001018371A1 (en) * 1999-09-07 2001-03-15 Geza Vermes Ambient pressure gas turbine system
US20020148232A1 (en) 2000-02-24 2002-10-17 Willis Jeffrey W. Gas turbine engine having a multi-stage multi-plane combustion system
US20040098965A1 (en) * 2002-11-27 2004-05-27 Dettmer Gregory Brian Microturbine direct fired absorption chiller
US20100000218A1 (en) 2003-06-19 2010-01-07 Hitachi, Ltd. Gas turbine combustor and fuel supply method for same
US20090019855A1 (en) 2006-05-04 2009-01-22 General Electric Company Low emissions gas turbine combustor
US20100126174A1 (en) 2006-09-07 2010-05-27 Rainer Brinkmann Gas turbine combustion chamber
US20100071377A1 (en) 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014134182A3 (en) * 2013-02-26 2014-11-06 Electric Jet, Llc Micro gas turbine engine for powering a generator
US9267437B2 (en) 2013-02-26 2016-02-23 Electric Jet, Llc Micro gas turbine engine for powering a generator
US10948190B2 (en) 2015-09-30 2021-03-16 IFP Energies Nouvelles Combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for producing energy, in particular electrical energy
CN108027144A (en) * 2015-09-30 2018-05-11 Ifp新能源公司 The combustion chamber of turbine, especially with thermodynamic cycle turbine recuperative, for producing electricl energy
EP3356737B1 (en) * 2015-09-30 2022-05-25 IFP Energies nouvelles Thermodynamic cycle turbine with recuperator, for producing electrical energy
FR3041742A1 (en) * 2015-09-30 2017-03-31 Ifp Energies Now COMBUSTION CHAMBER FOR A TURBINE, IN PARTICULAR A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, ESPECIALLY ELECTRICAL ENERGY.
WO2017055074A1 (en) * 2015-09-30 2017-04-06 IFP Energies Nouvelles Combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for producing energy, in particular electrical energy
CN108779918A (en) * 2016-03-18 2018-11-09 Ifp新能源公司 For generate energy, particularly electric energy turbine, especially include storage heater the turbine with thermodynamic cycle combustion chamber
CN108779918B (en) * 2016-03-18 2020-10-30 Ifp新能源公司 Turbine for generating energy and combustion chamber thereof
FR3049044A1 (en) * 2016-03-18 2017-09-22 Ifp Energies Now COMBUSTION CHAMBER FOR A TURBINE, IN PARTICULAR A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, ESPECIALLY ELECTRICAL ENERGY.
WO2017157631A1 (en) 2016-03-18 2017-09-21 IFP Energies Nouvelles Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy
WO2018041454A1 (en) 2016-08-29 2018-03-08 IFP Energies Nouvelles Modular turbine, in particular turbine with heat exchanger for producing energy, in particular electrical energy
WO2018041455A1 (en) 2016-08-29 2018-03-08 IFP Energies Nouvelles Combustion chamber with a hot compressed air deflector, in particular for a turbine intended for producing energy, in particular electrical energy
CN109642729A (en) * 2016-08-29 2019-04-16 Ifp新能源公司 Especially for being intended to generate the combustion chamber with hot compression formula air deflector of the turbine of energy, particularly electric energy
CN109642729B (en) * 2016-08-29 2021-11-02 Ifp新能源公司 Turbine for energy production and combustion chamber thereof
US11162422B2 (en) 2016-08-29 2021-11-02 IFP Energies Nouvelles Combustion chamber with a hot compressed air deflector, in particular for a turbine intended for producing energy, in particular electrical energy
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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