Fuel injector

1. A fuel injector, comprising:

a member defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, wherein the member is disposed in a space between a liner and a flow sleeve disposed about the liner through which a liner flow travels such that the elongate and short axes are disposed at complementary angles that are each between 0 and 90 degrees with respect to the liner flow;

a head defining a plenum storing a supply of a second fluid; and

a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum at injection locations defined in the member about a periphery of the flowpath at first and second locations along the elongate axis and into the flowpath,

the injected second fluid being formed into jets at the first and second locations, the first fluid entraining the jets such that the injected second fluid flows through the flowpath and mixes with the first fluid, and the short axis having a sufficient dimension such that the jets remain spaced from a sidewall of the member.

2. The fuel injector according to claim 1 , wherein the first fluid comprises air and the second fluid comprises fuel.

3. A fuel injector, comprising:

a member defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, wherein the member is disposed in a space between a loner and a flow sleeve disposed about the liner through which a liner flow travels such that the elongate and short axes are disposed at complementary angles that are each between 0 and 90 degrees with respect to the liner flow;

a head defining a plenum storing a supply of a second fluid; and

a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum and into the plenum at first and second locations along the elongate axis,

the injected second fluid being formed into jets at the first and second locations, the first fluid entraining the jets such that the injected second fluid flows through the flowpath and mixes with the first fluid, and the short axis having a sufficient dimension such that the jets remain spaced from a sidewall of the member,

wherein the system comprises a portion of the sidewall of the member defining first and second through-holes at the first and second locations, respectively through which the second fluid is injected into the flowpath.

4. The fuel injector according to claim 3 , wherein the first and second through-holes are defined on one or both sides of the flowpath.

5. The fuel injector according to claim 1 , wherein the system comprises a blade supported by the head, the blade defining:

a blade interior, which is fluidly communicative with the plenum, and

first and second injection-holes at the first and second locations, respectively, through which the second fluid is injected into the flowpath.

6. The fuel injector according to claim 5 , wherein the first and second injection-holes are defined on one or both sides of the blade.

7. The fuel injector according to claim 5 , wherein the blade has an airfoil shape.

8. The fuel injector according to claim 5 , wherein the blade comprises a blade matrix including transverse central and auxiliary blades.

9. The fuel injector according to claim 1 , wherein an outer surface of the member has a shape similar to that of the flowpath.

10. The fuel injector according to claim 1 , wherein an outer surface of the member has a shape different from that of the flowpath.

11. The fuel injector according to claim 10 , wherein the outer surface of the member has an airfoil shape.

12. The fuel injector according to claim 1 , wherein the member has an evolving shape along a longitudinal axis thereof.

13. A portion of a gas turbine engine, comprising:

a vessel including a liner defining an interior through which a main flow travels and a flow sleeve disposed about the liner to define a space through which a liner flow travels; and

a fuel injector to injector fuel and air into the main flow, the fuel injector including a member traversing the space and defining an elongate flowpath through which the fuel and air flow toward the main flow, the elongate flowpath having a cross-section defined in parallel with a direction of flow of the loner flow through the space with transverse elongate and short axes,

the member including an outer surface having an elongate shape, wherein the member is disposed in the space such that the elongate and short axes are disposed at complementary angles that are each between 0 and 90 degrees with respect to the liner flow.

14. The portion of the gas turbine engine according to claim 13 , wherein the fuel injector is plural in number, the plural fuel injectors being arrayed circumferentially about the main flow.

15. The portion of the gas turbine engine according to claim 14 , wherein each member of each of the plural fuel injectors is similarly angled with respect to the liner flow.

16. The portion of the gas turbine engine according to claim 13 , wherein the flowpath and the member have similar shapes.

17. A portion of a gas turbine engine, comprising:

a vessel including a liner defining an interior through which a main flow travels and a flow sleeve disposed about the liner to define a space through which a liner flow travels; and

a fuel injector, including:

a member traversing the space and defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, wherein the member is disposed in the space such that the elongate and short axes are disposed at complementary angles that are each between 0 and 90 degrees with respect to the liner flow;

a head defining a plenum storing a supply of a second fluid; and

a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum and into the flowpath at first and second locations along the elongate axis,

the injected second fluid being formed into jets at the first and second locations, the first fluid entraining the jets such that the injected second fluid flows through the flowpath toward the main flow and mixes with the first fluid, and the short axis having a sufficient dimension such that the jets remain spaced from a sidewall of the member.

18. The portion of the gas turbine engine according to claim 17 , further comprising a foot of the member, the head being supportively coupled to or integrally formed with the flow sleeve and the foot being supportively coupled to or integrally formed with the liner.