1. A fuel nozzle comprising:
a centerbody having an inlet end and a discharge end for discharging an airfuel mixture into a combustion chamber; and
a heat shield positioned within a central passage of said centerbody and having a first end at said inlet end and a second end at said discharge end, wherein an outer surface of said heat shield is fixed to an inner surface of said centerbody at a mid-mount position located generally centrally between said first end and said second end.
2. The fuel nozzle according to claim 1 wherein said first and said second ends are movable relative to said centerbody in an axial direction to accommodate thermal expansion.
3. The fuel nozzle according to claim 1 wherein said mid-mount position is generally equally spaced from each of said first and said second ends.
4. The fuel nozzle according to claim 1 including an inner air swirler mounted to an inner surface of said heat shield at one attachment interface and wherein said heat shield is fixed to said centerbody at another attachment interface comprising said mid-mount position which is axially spaced from said one attachment interface.
5. A fuel nozzle comprising:
a centerbody having an inlet end and a discharge end for discharging an airfuel mixture into a combustion chamber, said centerbody defining a central axis;
a heat shield fixed to said centerbody at a first attachment interface; and
an inner air swirler fixed to said heat shield at a second attachment interface axially spaced from said first attachment interface in a direction along said central axis and wherein said first attachment interface is positioned axially between said second attachment interface and said discharge end of said centerbody.
6. The fuel nozzle according to claim 5 wherein said heat shield has a first end at said inlet end and a second end at said discharge end with said inner air swirler being fixed to an inner surface of said heat shield adjacent said first end to form said second attachment interface and with an outer surface of said heat shield being fixed to said centerbody at centrally located position between said first and said second ends to form said first attachment interface.
7. The fuel nozzle according to claim 6 wherein said outer surface of said heat shield is radially spaced apart from an inner surface of said centerbody to form an air gap that extends along a substantial length of said heat shield.
8. The fuel nozzle according to claim 6 wherein said first and said second ends of said heat shield have slip fit interfaces with said centerbody to allow said heat shield to expand in an axial direction along said central axis.
9. The fuel nozzle according to claim 5 wherein said heat shield includes a raised boss portion extending radially outwardly from an outer surface of said heat shield, said raised boss portion being directly attached to an inner surface of said centerbody.
10. The fuel nozzle according to claim 5 wherein said heat shield is fixed to said centerbody by brazing.
11. A gas turbine engine comprising:
a fan;
a compressor;
a turbine; and
a combustion section including a plurality of fuel nozzles wherein each fuel nozzle includes a centerbody defining a central axis and having an inlet end and a discharge end for discharging an airfuel mixture into a combustion chamber, a heat shield fixed to said centerbody at a first attachment interface, and an inner air swirler fixed to said heat shield at a second attachment interface axially spaced from said first attachment interface in a direction along said central axis, and wherein said first attachment interface is positioned axially between said second attachment interface and said discharge end of said centerbody.
12. The gas turbine engine according to claim 11 wherein said heat shield has a first end at said inlet end and a second end at said discharge end with said inner air swirler being fixed to an inner surface of said heat shield adjacent said first end to form said second attachment interface, and with an outer surface of said heat shield being fixed to said centerbody at a centrally located position between said first and said second ends to form said first attachment interface.
13. The gas turbine engine according to claim 12 wherein said first and said second ends of said heat shield have slip fit interfaces with said centerbody to allow said heat shield to expand in an axial direction along said central axis.
14. The gas turbine engine according to claim 13 wherein said outer surface of said heat shield is radially spaced apart from an inner surface of said centerbody to form an air gap that extends along a substantial length of said heat shield.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A system for conditioning a space within an environment, the system comprising:
a solid boundary;
at least one air supply aperture configured to direct a conditioned airflow towards the solid boundary; and
at least one air return aperture configured to receive a return airflow, wherein:
at least one of the conditioned airflow or the return airflow creates an air boundary, such that the air boundary and the solid boundary define the space within the environment, and
at least a portion of the conditioned airflow enters the space, and at least a portion of the return airflow exits the space, thereby conditioning the space.
2. The system of claim 1, wherein the solid boundary comprises a solid surface.
3. The system of claim 1, wherein the at least one air supply aperture comprises at least one hole, slit, slot, nozzle, vent, or register.
4. The system of claim 1, wherein the conditioned airflow has a flow rate from about 1 CFM to about 1000 CFM.
5. The system of claim 4, wherein the conditioned airflow is divided into a plurality of smaller airflows by the air supply aperture comprising a plurality of smaller air supply apertures.
6. The system of claim 5, wherein each of the plurality of smaller airflows has a gas velocity ranging from about 1 ftsec to about 100 ftsec.
7. The system of claim 1, wherein the conditioned airflow is conditioned by at least one of heating, cooling, humidifying, or dehumidifying.
8. The system of claim 1, wherein the at least one air return aperture comprises at least one hole, slit, slot, nozzle, vent, or register.
9. The system of claim 1, wherein the return airflow has a flow rate from about 1 CFM to about 1000 CFM.
10. The system of claim 1, wherein the portion of the conditioned airflow ranges from about 1 vol % to about 100 vol % of the conditioned airflow.
11. The system of claim 1, wherein the portion of the return airflow ranges from about 1 vol % to about 100 vol % of the return airflow.
12. The system of claim 1, wherein the space is configured to accommodate a human lying substantially in a prone position within at least a portion of the space.
13. A method for conditioning a space within an environment, the method comprising:
directing a conditioned airflow towards a solid boundary;
receiving a return airflow; and
defining the space by the conditioned airflow, the return airflow, and the solid boundary, wherein:
the conditioned airflow comprises a portion that is directed into the space and the return air flow comprises a portion that is received from the space, thereby conditioning the space.