Assembly having a gas turbine engine and a preheating arrangement

1. An assembly comprising:

a gas turbine and a heat exchanger for heating up a gas turbine process fluid by thermal energy, said gas turbine comprising a compressor, a combustor and a turbine downstream said combustor,

wherein said assembly comprises a first line to conduct said gas turbine process fluid from said compressor to said heat exchanger, and

wherein said assembly comprises a second line to conduct said gas turbine process fluid from said heat exchanger to said combustor to generate hot combustion gas from warmed up gas turbine process fluid burning fuel in said combustor,

wherein said combustor is defined by a first shell element containing a main combustion zone,

wherein said combustor is at least partly surrounded by a second shell element to provide an annular channel between said first shell element and said second shell element as a part of said first line.

2. The assembly according to claim 1 ,

wherein said first line and said second line exchange heat.

3. The assembly according to claim 2 ,

wherein said first line and said second line are arranged coaxially to each other along at least a portion of their respective length.

4. The assembly according to claim 1 ,

wherein flow directions of said gas turbine process fluid in said first line and said second line are contrary.

5. The assembly according to claim 1 ,

wherein said combustor comprises a burner upstream said main combustion zone, wherein said burner comprises main fuel nozzles to supply said fuel by the main fuel nozzles and at least one pilot injector to ignite and/or maintain combustion by said at least one pilot injector.

6. The assembly according to claim 5 ,

wherein said combustor comprises a central axis extending along a main flow direction of said gas turbine process fluid through said combustor,

wherein said at least one pilot injector injects said fuel along a first inclination angle α1 to said central axis,

wherein: 0°<α1<45°.

7. The assembly according to claim 6 ,

wherein said main fuel nozzles inject said fuel along a second inclination angle α2 to said central axis,

wherein: α2 >α1.

8. The assembly according to claim 7 ,

wherein: 0°<α1<10° and 45°<α2<120°.

9. The assembly according to claim 8 ,

wherein said burner comprises fuel injection devices respectively comprising at least one pilot injector and/or at least one main fuel nozzle and respectively connected to a fuel supply line,

wherein said fuel injection devices are arranged in an axial plane perpendicular to said central axis.

10. The assembly according to claim 9 ,

wherein the fuel injection devices occupy a part area of a cross sectional area perpendicular to said central axis of said combustor, thereby restricting a free cross sectional area available for a flow of said gas turbine process fluid, and

wherein a front face's part area of each fuel injection device facing oppositely the flow of said gas turbine process fluid is covered by a respective flow contour extending axially such that a constriction of said free cross sectional area by the fuel injection devices is made continuously along at least a part of an axial extension of said fuel injection devices.

11. The assembly according to claim 10 ,

wherein an enlargement of said free cross sectional area by the fuel injection devices and downstream of respective at least one main fuel nozzles is made more abrupt than the constriction by said flow contours.

12. The assembly according to claim 7 ,

wherein: 0°<α1<10° and α2=90°.