1. A automated method for preparing a plurality of targets for hybridization to a microarray comprising:
incubating nucleic acid probes in a hybridization buffer so that the nucleic acid probes bind to the surface of a substrate, wherein the hybridization buffer comprises tetramethyl ammonium chloride (TMAC).
2. The method of claim 1, wherein the hybridization buffer further comprises MES, EDTA and Tween 20.
3. The method of claim 1, wherein nucleic acid comprises of cRNA or cDNA
4. The method of claim 1, wherein the concentration of TMAC is between about 1 M to about 4M.
5. The method of claim 1, wherein the concentration of MES is between about 50 mM and 200 mM.
6. The method of claim 1, wherein the concentration of EDTA is between 5 mM and 40 mM.
6. The method claim 1, wherein the concentration of Tween is between 0.001% and 0.5%.
7. The method of claim 1, wherein the incubation temperature is about 40 to 55\xb0 C.
8. The method of claim 1, wherein the incubation time is between 10 and 20 hours.
9. A microarray hybridization buffer comprising betwee 75 and 150 mM MES, between 15 and 30 mM EDTA, between 0.001 and 0.02% Tween 20, and between 2 and 3 M TMAC and optionally comprising herring sperm DNA, acetylated BSA, Denhardt’s solution and human cot-1 DNA.
10. An array holding buffer comprising about 60 to 80 mM MES, about 0.8 to 1.2 M NaCl, and about 0.005 to 0.02% Tween.
11. A method for preparing amplified and labeled cRNA from a plurality of RNA samples in parallel comprising:
synthesizing first strand cDNA from the RNA using reverse transcriptase and a T7 promoter primer;
synthesizing second strand cDNA using a DNA polymerase and RNase H to obtain double stranded cDNA with a T7 RNA polymerase promoter;
cleaning the double stranded cDNA using solid phase reversible immobilization to magnetic beads;
eluting the cleaned double stranded cDNA from the magnetic beads; and
mixing the cleaned double stranded cDNA in a reaction comprising T7 RNA polymerase and labeled nucleotides to generate cRNA.
12. The method of claim 11 wherein at least 8 samples are analyzed.
13. The method of claim 11 wherein at least 24 samples are analyzed.
14. The method of claim 11 wherein at least 96 samples are analyzed.
15. The method of claim 11 wherein the cRNA is labeled with biotin.
16. The method of claim 11 wherein the samples are processed on an automated liquid handling robot.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
What is claimed is:
1. A combustor dome module for a gas turbine engine combustor comprising:
an annular pre-vaporizing chamber defined by an outer wall, an inner wall, and a heat shield, said heat shield including an opening adapted to allow a fuel to pass into a piloting flame stability region of the gas turbine engine combustor;
an outer swirler coupled to said outer wall of said pre-vaporizing chamber; and
an inner swirler coupled to said inner wall of said pre-vaporizing chamber.
2. The combustor dome module of claim 1, wherein said inner swirler is formed integral with said inner wall member of said pre-vaporizing chamber, and said outer swirler is formed integral with said outer wall member of said pre-vaporizing chamber.
3. The combustor dome module of claim 1, wherein said heat shield is made of a ceramic material and floats relative to at least one of said inner and outer wall members of said pre-vaporizing chamber.
4. The combustor dome module of claim 1, wherein said inner and outer swirlers are radial or axial inflow bulk swirlers.
5. The combustor dome module of claim 1, wherein said inner swirler is adapted to impart a swirl to a flow discharged therefrom in a direction that is the same as, or opposite, that imparted to a flow discharged from said outer swirler.
6. The combustor dome module of claim 1, wherein each of said swirlers discharges a flow that recirculates toward said heat shield, thereby creating a double vortex.
7. A combustor for a gas turbine engine comprising:
a combustion chamber having an annular configuration defined by an inner wall and an outer wall;
a combustor dome module coupled to said inner and outer walls of said combustion chamber, said combustor dome module including an annular pre-vaporizing chamber defined by an inner wall member, an outer wall member, and a heat shield; and
means disposed in said pre-vaporizing chamber for delivering a fuel into said pre-vaporizing chamber.
8. The combustor of claim 7, wherein said heat shield includes an opening to allow fuel to pass into a piloting flame stability region of said combustion chamber.
9. The combustor of claim 7, further comprising an inner swirler coupled to said inner wall member of said pre-vaporizing chamber, and an outer swirler coupled to said outer wall member of said pre-vaporizing chamber.
10. The combustor of claim 9, wherein said inner swirler is formed integral with said inner wall member of said pre-vaporizing chamber, and said outer swirler is formed integral with said outer wall member of said pre-vaporizing chamber.
11. The combustor of claim 9, further comprising inner and outer cowlings coupled to said combustor dome module and defining a fluid flow passageway for passage of a pressurized working fluid to said inner and outer swirlers.
12. The combustor of claim 9, wherein said inner and outer swirlers are radial or axial inflow bulk swirlers.
13. The combustor of claim 9, wherein said inner swirler is adapted to impart a swirl to a flow discharged therefrom in a direction that is the same as, or opposite, that imparted to a flow discharged from said outer swirler.
14. The combustor of claim 9, wherein each of said swirlers discharges a flow that recirculates forward toward said heat shield, thereby creating a double vortex.
15. The combustor of claim 9, wherein a vaporized fuel and air mixture exiting said pre-vaporizing chamber enters said combustion chamber between said heat shield and said swirlers.
16. The combustor of claim 9, wherein a vaporized fuel and air mixture exiting said pre-vaporizing chamber is directed through said swirlers before entering said combustion chamber.
17. The combustor of claim 9, wherein a flow of fuel is sprayed into said combustion chamber through said swirler vanes.
18. The combustor of claim 7, wherein said means for delivering fuel into said pre-vaporizing chamber includes at least one fuel nozzle with at least one opening oriented to spray fuel onto said heat shield, whereby the fuel is normally vaporized upon reaching the heat shield.
19. The combustor of claim 18, wherein said at least one opening numbers nine.
20. The combustor of claim 7, wherein said means for delivering fuel into said pre-vaporizing chamber includes a plurality of fueling nozzles spaced around said annular pre-vaporizing chamber.
21. The combustor of claim 20, wherein said plurality of fueling nozzles numbers eight.
22. The combustor of claim 7, wherein said heat shield is made of a ceramic material and floats relative to said inner and outer wall members of said pre-vaporizing chamber.
23. A gas turbine engine combustor comprising:
a pre-mixing zone;
a reaction zone;
a heat shield separating said pre-mixing zone from said reaction zone, said heat shield having an outer surface in said pre-mixing zone; and
a fueling nozzle disposed in said pre-mixing zone for spraying fuel onto said outer surface of said heat shield, thereby cooling said heat shield.
24. The combustor of claim 23, wherein said reaction zone has an annular configuration.
25. The combustor of claim 23, wherein said pre-mixing zone has an annular configuration.