Claims
- 1. A fuel air mixer for a gas turbine engine combustor having a longitudinal axis therethrough, comprising:(a) a fuel injection assembly having a first end, a second end, a fuel passage extending therethrough, and a flange portion having a plurality of spaced openings formed therein which extends from said first end, said fuel injection assembly further comprising: (1) an elongated fuel stem extending from said first end to said second end, said fuel stem including said fuel passage from said first end to said second end; (2) a fuel inlet in flow communication with said fuel passage in said fuel stem adjacent said first end thereof; and (3) a plurality of fuel injectors in flow communication with said fuel passage in said fuel stem adjacent said second end thereof; wherein fuel entering said fuel air mixture at said fuel inlet is provided through said fuel stem passage and injected into a combustion zone through said fuel injectors; and(b) a mixture assembly having a first end, a second end, a cavity formed in a central portion thereof, and a flange portion having a plurality of spaced openings formed therein which extends from said first end; wherein said mixer assembly is configured to receive said fuel injection assembly in said cavity so that said fuel injection assembly and said mixture assembly are able to be connected to a casing of said combustor by means of said flange portions.
- 2. The fuel air mixer of claim 1, said mixer assembly further comprising:(a) an elongated mixer tube having a cavity extending from said first end to said second end, said mixer tube including a plurality of first openings formed therein in flow communication with an air supply to an outer annular portion of said combustor and a plurality of second openings formed therein adjacent said second end thereof so as to be alignable with said fuel injectors; and (b) an end wall extending across said a lower portion of said cavity adjacent said second end.
- 3. The fuel air mixer of claim 2, wherein said fuel stem has a lower portion with a reduced diameter so as to form a passage with said mixer tube which is in flow communication with said mixer tube first openings and enables air to be mixed with fuel as it is injected through said mixer tube second openings.
- 4. The fuel air mixer of claim 2, said flange portions of said fuel injection assembly and said mixer assembly each including an additional opening formed therein so as to ensure proper alignment and orientation of said fuel injectors and said mixer assembly second openings when aligned and coupled.
- 5. The fuel air mixer of claim 2, said fuel mixer further comprising a heat shield attached to a lower portion of said mixer assembly.
- 6. The fuel air mixer of claim 5, said heat shield further comprising:(a) a substantially annular wall portion configured so as to receive a lower portion of said mixer tube, said annular wall portion of said heat shield including a plurality of openings formed therein and configured so as to be alignable with said second openings in said mixer tube; and (b) an end wall across a lower end of said annular wall portion; wherein said heat shield and said mixer assembly are connected by means of a tube inserted through each said mixer assembly second opening and said heat shield openings so as to form a cavity between said mixer end wall and said heat shield end wall.
- 7. The fuel air mixer of claim 6, wherein said tubes are connected only to said heat shield openings so that a slip joint is formed by said tubes and said mixer tube second openings to accommodate transverse movement of said mixer tube.
- 8. The fuel air mixer of claim 6, wherein said heat shield and said mixer tube are configured so as to form an air flow passage therebetween which is in flow communication with said cavity.
- 9. The fuel air mixer of claim 6, wherein said heat shield end wall is provided with thermal barrier coating.
- 10. The fuel air mixer of claim 6, wherein said heat shield end wall includes a plurality of openings formed therein so that air flowing into said cavity is directed into said combustion zone.
- 11. The fuel air mixer of claim 6, wherein said heat shield and said radial dome form a throat area therebetween in flow communication with a fuel air mixture provided through said tubes connecting said mixer tube and said heat shield.
- 12. The fuel air mixer of claim 11, wherein said annular wall portion of said heat shield includes a plurality of openings formed therein adjacent said end wall so that air entering said cavity is provided into said throat area.
CROSS-REFERENCE TO RELATED APPLICATIONS
This application is related to provisional applications having Ser. No. 60/103,652 filed Oct. 9, 1998 and Ser. No. 60/103,649, filed Oct. 10, 1998.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH AND DEVELOPMENT
The U.S. Government may have certain rights in this invention pursuant to contract number NAS3-27235, NAS3-26617, and/or NAS3-25951.
US Referenced Citations (10)
Foreign Referenced Citations (2)
Number |
Date |
Country |
893650 |
Jan 1999 |
EP |
788642 |
Nov 1935 |
FR |
Non-Patent Literature Citations (1)
Entry |
“HSCT Computer Model Takes Shape ar NASA,” pp. 68-76, by James Ott, Hampton VA, in Aviation Week & Space Technology, Oct. 13, 1997. |
Provisional Applications (2)
|
Number |
Date |
Country |
|
60/103652 |
Oct 1998 |
US |
|
60/103649 |
Oct 1998 |
US |