Method and gas turbine combustion system for safely mixing H2-rich fuels with air

Abstract

A method and apparatus are disclosed for mixing H2-rich fuels with air in a gas turbine combustion system, wherein a first stream of burner air and a second stream of a H2-rich fuel are provided. All of the fuel is premixed with a portion of the burner air to produce a pre-premixed fuel/air mixture. This pre-premixed fuel/air mixture is injected into the main burner air stream.

Claims

1. A method for mixing H2-rich fuels with air in a gas turbine combustion system having a combustion chamber with a burner, comprising: providing a first stream of burner air, branched from a stream of compressor air, and a second stream of a H2-rich fuel, wherein the first stream of burner air is not used for liner cooling; pre-premixing all of the H2-rich fuel to be injected with the first stream of burner air to produce a pre-premixed fuel/air mixture; and providing a main air stream, taken from the stream of compressor air and used for liner cooling before entering the burner; and in the burner, injecting the pre-premixed fuel/air mixture into the main air stream and premixing the pre-premixed fuel/air mixture and the main air to form a premixture within the burner which enters the combustion chamber; wherein the pre-premixed fuel/air mixture is injected in an axial direction that is in a cross-flow direction with respect to a direction of injection of the main air stream flow, wherein an air excess factor of A>1, is achieved in the premixing in the burner.

2. The method according to claim 1, wherein the premixing is done in a manner for preventing flame anchoring at undesired locations, including at least one of near an injection location and in the burner.

3. The method according to claim 1, comprising: separating air into O2 and N2 with an air separation unit; and adding a portion of the N2 from the air separation unit to at least one of the main burner air and the pre-premixed fuel/air mixture.

4. The method according to claim 1, comprising: using a pre-premixer formed as a channel with straight air flow to avoid at least one of recirculation and stagnation regions to produce the pre-premixed fuel/air mixture.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The present disclosure is now to be explained more closely by different embodiments and with reference to the attached drawings.

(2) FIG. 1 shows laminar flame speeds for CH4 (a known gas turbine fuel) and for various H2/N2 mixtures at 1 atm and 20 C.;

(3) FIG. 2 illustrates a pre-premixing according to an exemplary embodiment of the disclosure;

(4) FIG. 3 shows an exemplary embodiment of a burner encompassing a pre-premixing concept according to the disclosure; and

(5) FIG. 4 illustrates an exemplary embodiment of the disclosure wherein a main swirler in a swirl-stabilized burner can be utilized to further increase the velocity in a pre-premixer, by taking advantage that a local static pressure in a central region of the burner is lower than a nominal burner pressure.

DETAILED DESCRIPTION

(6) An exemplary embodiment of the disclosure provides a method for safely mixing H2-rich fuels with air in gas turbine combustion systems (e.g., to provide safe mixing), which can effectively permit the local fuel/air mixture to bypass the peak burning velocity (i.e., =0.6) prior to injection into the main burner air stream (known as liner air).

(7) A method according to an exemplary embodiment of the disclosure includes: providing a first stream of burner air and a second stream of a H2-rich fuel, premixing the fuel (e.g., all of the fuel) with a portion of the burner air to produce a pre-premixed fuel/air mixture, and injecting this pre-premixed fuel/air mixture into the main burner air stream.

(8) According to an exemplary embodiment of the disclosure, the premixing can be done in a manner which can prevent flame anchoring at undesired locations, especially near the injection location and in the burner.

(9) According to an exemplary embodiment of the disclosure, an air excess factor of >1, for example, >1.3, can be achieved in the premixing step.

(10) According to an exemplary embodiment of the disclosure, air can be separated into O2 and N2 by an air separation unit (ASU), and a portion of the N2 from the air separation unit (ASU) can be added to the main burner air and/or pre-premixed fuel/air mixture.

(11) According to an exemplary embodiment of the disclosure, a pre-premixer can be in the form of a simple (for example, round) channel with straight or slightly swirling air flow can be used to avoid recirculation and/or stagnation regions.

(12) According to an exemplary embodiment of the disclosure, a pre-premixer including narrow channels whose hydraulic diameter D is less than the quenching distance Q, can be used.

(13) According to an exemplary embodiment of the disclosure, the boundary layers of the air flow in the pre-premixer can be energized, for example, by using some film air, in order to increase velocities in these regions.

(14) According to an exemplary embodiment of the disclosure, the air flow can be additionally accelerated via a jet-pump effect of injecting large volumes of H2/N2 fuel.

(15) According to an exemplary embodiment of the disclosure, water mist can be injected into the H2-rich fuel to enhance the safety of the method by the relative cooling due to the subsequent evaporation of the injected water.

(16) According to an exemplary embodiment of the disclosure, a main swirler in a swirl-stabilized burner can be utilized to further increase the velocity in the pre-premixer by taking advantage that the local static pressure in the central region of the burner can be lower than the nominal burner pressure.

(17) A gas turbine combustion system for applying the method according to exemplary embodiments of the disclosure can include a combustion chamber and at least one burner opening into the combustion chamber to inject a stream of burner air into the combustion chamber, at least one pre-premixer for providing a pre-premixed fuel/air mixture, whereby the at least one burner and the at least one pre-premixer can be arranged relative to each other, such that the pre-premixed fuel/air mixture can be injected into the stream of burner air.

(18) According to an exemplary embodiment of the gas turbine combustion system the at least one pre-premixer can have the form of a simple (for example, round), channel with straight or slightly swirling air flow.

(19) According to an exemplary embodiment of the gas turbine combustion system, the at least one pre-premixer can include narrow channels whose hydraulic diameter can be less than a quenching distance.

(20) According to an exemplary embodiment of the gas turbine combustion system, the at least one burner can be a swirl-stabilized burner.

(21) According to an exemplary embodiment of the gas turbine combustion system, the at least one burner can be a so-called Environmental (EV) burner (in place of many: EP 0 321 809 B1) or a so-called Advanced Environmental (AEV) burner (in place of many: EP 0 704 657).

(22) According to an exemplary embodiment of the gas turbine combustion system, the at least one burner can be a so-called Sequential Environmental (SEV) burner (in place of many: EP 0 620 362 B1, pos. 5).

(23) All of these documents mentioned herein relating to EV-, AEV- and SEV-burners and all these developed improvements, patent applications and patents, form an integrating component of this patent application, and incorporated herein by reference in their entireties.

(24) The exemplary embodiments of the disclosure relate to premixing the fuel with a portion of burner air (denoted as pre-premixing air) in a manner which can prevent flame anchoring, and then injecting this fuel/air mixture (characterized by >1, for example, >1.3) into the main burner air stream (i.e., the liner air). This can be done in one or more stages. FIG. 2 illustrates an exemplary embodiment of the concept (which is called pre-premixing). P_pk2 and T_pk2 are the pressure and temperature, respectively, at a compressor exit of the gas turbine. P_fuel and T_fuel are the pressure and temperature, respectively, of the fuel, T_mix is the temperature of the pre-premixing mixture, while P_hood and T_hood are the pressure and temperature, respectively, of the hood air (which is the air that enters the burner). The pre-premixing method can involve elements of the traditional solutions for H2-rich fuels (for example, high air velocities, high dilution levels), but the negative effects can be rather limited because these methods can apply to a portion of the overall burner air (i.e., the pre-premixing air), rather than the entire burner air flow.

(25) Mass and energy balances show that about 25% and 45% of the total burner air is needed such that the pre-premixed fuel/air has a of 0.6 and 1.0, respectively, for a 70/30 H2/N2 fuel (air temperature 420 C., fuel temperature 150 C., T_ad=1750K).

(26) In the event that the resulting liner cooling is insufficient (because part of the compressor air was diverted to the pre-premixer), it would be possible to add the remaining N2 from the ASU (air separation unit) to the liner air, the mixture temperature of which would be significantly below the standard liner air temperature of 400 C. This stream of N2 would only have to be compressed from the ASU pressure (approx. 5 bar for a low-pressure device, or 15 bar for a high-pressure ASU) to the P_pk2 pressure (i.e., at compressor exit).

(27) The pre-premixing process is driven by a pressure loss (AP) that is larger than that across the burner. FIG. 2based on a GT13E2 gas turbine of the applicant under full-load conditions for an AEV-125 burnershows that this pressure loss can be proportional to the sum of the liner and swirler pressure losses, P_liner and P_swirler, amounting to P2 to 3%.

(28) Further safety benefits of the pre-premixing concept are noted.

(29) The relatively cold fuel is mixed with only a portion of the entire burner air, meaning that the pre-premixed mixture temperature T_mix is significantly lower (278 C. and 310 C. for =0.6 and 1.0, respectively, compared to 350 C. when the fuel is mixed with all the burner air (based on 70/30 H2/N2 at 150 C.). This reduces the reactivity of the air/fuel mixture, thereby greatly assisting the safe transition to 1).

(30) The pre-premixing air stream is cooler than the hood air (by around 20 C.), because it is not used for liner cooling. This can further reduce reactivity in the pre-premixer.

(31) If N2 is used for a part of the pre-premixing air, then the risk of ignition can be reduced due to lower O2; and lower temperature; and the pre-premixed mixture can achieve greater penetration depths in the burner (due to the higher fuel mass flow rates relative to the air mass flow), thereby permitting better mixing than when the non-pre-premixed fuel is injected into the burner.

(32) Several methods of achieving the desired pre-premixing are described below. There are other methods of achieving the proposed idea, which will be apparent to those skilled in the art.

(33) The pre-premixer (16 in FIG. 4) can include a simple channel (for example, round) with straight air flow. Aerodynamically simple geometries can avoid recirculation and/or stagnation regions. The boundary layers can be energized (for example, using some film air) in order to increase velocities in these regions. Both jets in cross-flow and co-flowing jets can be used. The latter can further reduce risk of flame anchoring.

(34) Lack of swirl in the pre-premixer means that the air velocity can be around 50% higher than that in the burner (approx 120 m/s), using the given AP.

(35) The air flow can additionally be accelerated via the jet-pump effect of injecting large volumes of H2/N2 fuel.

(36) The pre-premixer can include small channels whose hydraulic diameter is less than the quenching distance. Injection and pre-mixing of the fuel in these small channels can prevent homogeneous ignition from occurring during the mixing process and prior to the attainment of higher . The air velocity can be small, because safety can now be promoted by quenching rather than by convection. Small air velocities in narrow channels are compatible with the available P.

(37) An injection of water into H2-rich fuel and relative cooling by subsequent evaporation would further enhance the safety of the present methodology.

(38) FIG. 3 is an example of a burner encompassing the new pre-premixing concept described above. According to FIG. 3, in a combustion system 10, a pre-premixed fuel/air mixture C is injected through pre-premixers 11 and 12 into a burner 17 which opens into a combustion chamber 13. Main air 22 is added through main burner air inlets 14 and 15 near the exit of the pre-premixers 11, 12. The pre-premixing concept can of course be adapted to known burners such as the AEV and also the SEV. For example, see exemplary embodiments below. One or more pre-premixers may be provided per burner.

Embodiment 1

(39) The idea can be used for SEV (i.e. reheat) combustion as well. In this case, the pre-premixer temperature benefit would be even greater since the PK2 air used in the pre-premixer is colder (e.g., 400 C.-450 C.) than the 1000 C. of the main burner air. A similar benefit would be seen in the application to non-reheat lean-premix burners in recuperated combustion systems.

Embodiment 2

(40) Use less air in the pre-premixer. Whilst this gives <1, the local mixture temperature in the pre-premixer can be significantly smaller. This can compensate for the higher flame speeds associated with richer fuel/air mixtures. This can also leave more air for liner cooling.

Embodiment 3

(41) The pre-premixing concept can be applied to diffusion burners too. Such a configuration would permit clean and safe operation without derating (diffusion burners often have to run on lower firing temperatures for NOx reasons) and without the need for excessive dilution.

Embodiment 4

(42) The main swirler in a swirl-stabilized burner can be utilized to further increase the velocity (see dotted line B in FIG. 1) in the pre-premixer, simply by taking advantage of the fact that the local static pressure in the central region of the burner is lower than the nominal burner pressure. This is demonstrated in FIG. 4. According to FIG. 4, a combustion system 20 includes a burner 17 with a pre-premixer 16. A pre-premixed fuel/air mixture 21 generated within the pre-premixer 16 enters the burner 17 in an axial direction (axis 19). Main air 22 enters the burner 17 via a hood 18, thereby generating a swirl with a low static pressure region 24. The resulting fully premixed fuel/air mixture 23 exits the burner 17 to enter the subsequent combustion chamber. In general, the main air flow (i.e., hood or liner air) can enter the burner via axial, radial or hybrid swirlers.

(43) Thus, it will be appreciated by those skilled in the art that the present disclosure can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The presently disclosed embodiments are therefore considered in all respects to be illustrative and not restricted. The scope of the disclosure is indicated by the appended claims rather than the foregoing description and all changes that come within the meaning and range and equivalence thereof are intended to be embraced therein.

LIST OF REFERENCE NUMERALS

(44) 10,20 Combustion system 11,12 Pre-premixer 13 Combustion chamber 14,15 Main burner air inlet 16 Pre-premixer 17 Burner 18 Hood 19 Axis 21,C Pre-premixed fuel/air mixture 22,D Main air 23 Fully premixed fuel/air mixture 24 Low static pressure region