Combustor nozzle, combustor, and gas turbine

Patent metadata

Field	Value
Publication number	US-11274830-B2
Application number	US-201816491883-A
Country	US
Kind code	B2
Filing date	Mar 12, 2018
Priority date	Mar 13, 2017
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which extends along the axis and through which first fuel is configured to flow, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and is configured to eject the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured eject the purge air from the center of the distal end.

First claim

The invention claimed is:

1. A combustor nozzle comprising:
a nozzle main body extending along an axis,
wherein the nozzle main body includes:
a first fuel passage which extends along the axis and through which first fuel is configured to flow;
a plurality of first fuel ejection passages which extend to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and are configured to eject the first fuel from the outer circumferential surface of the nozzle main body;
an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow; and
an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured to eject the purge air from the center of the distal end of the nozzle main body, and
wherein the air ejection passage includes:
a plurality of upstream-side air ejection passages connected to the air flow passage;
an air cavity connected to downstream sides of the plurality of upstream-side air ejection passages; and
a downstream-side air ejection passage connecting the air cavity and the center of the distal end of the nozzle main body, the plurality of first fuel ejection passages and the plurality of upstream-side air ejection passages having different circumferential positions with respect to the axis and intersecting each other when viewed from a radial direction with respect to the axis.

2. The combustor nozzle according to claim 1 , wherein:
the air flow passage is an annular passage extending in a circumferential direction with respect to the axis; and
the first fuel passage is on a radial inner side of the air flow passage with respect to the axis.

3. The combustor nozzle according to claim 1 , further comprising an air insulation layer between the air flow passage and the first fuel passage.

4. The combustor nozzle according to claim 1 , wherein:
the nozzle main body includes a second fuel passage through which second fuel is configured to flow on the radial outer side of the first fuel passage with respect to the axis; and
the first fuel is oil fuel and the second fuel is gas fuel.

5. The combustor nozzle according to claim 1 , wherein the nozzle main body includes an air intake part which connects the outer circumferential surface of the nozzle main body and the air flow passage and is configured to take in the purge air from the outer circumferential surface of the nozzle main body.

6. The combustor nozzle according to claim 5 , further comprising a turning vane on the outer circumferential surface of the nozzle main body,
wherein the air intake part is defined in the nozzle main body on an upstream side of the turning vane.

7. A combustor comprising:
the combustor nozzle according to claim 5 ;
a combustor basket which holds the combustor nozzle and in which compressed air is configured to flow toward a downstream side; and
an outer shell defining a compressed air flow path which is configured to introduce the compressed air so as to be reversed at an end portion of the combustor basket and directed toward the downstream side between the combustor basket and the outer shell,
wherein:
the combustor nozzle includes a turning vane on the outer circumferential surface of the nozzle main body, the turning vane being configured to rectify the compressed air which has been reversed; and
the air intake part is defined in the nozzle main body on an upstream side of the turning vane.

8. The combustor according to claim 7 , wherein the air intake part is defined in the nozzle main body at a portion on a radial outer side with respect to a central axis of the combustor basket.

9. A combustor comprising:
the combustor nozzle according to claim 1 ;
a combustor basket which holds the combustor nozzle and in which compressed air is configured to flow toward a downstream side;
an outer shell defining a compressed air flow path which is configured to introduce the compressed air so as to be reversed at an end portion of the combustor basket and directed toward the downstream side between the combustor basket and the outer shell; and
an air intake part which is configured to supply the compressed air to the air flow passage.

10. A gas turbine comprising:
the combustor according to claim 9 ;
a compressor which is configured to generate compressed air in which air is compressed;
a turbine which is configured to be driven by a combustion gas generated by the combustor; and
an air supplier which is configured to generate compressed air,
wherein:
the air supplier includes an air extraction part which is configured to extract the compressed air generated by the compressor; and
the air intake part is configured to supply the compressed air generated by the air supplier to the air flow passage.

11. A combustor comprising:
a combustor basket which is cylindrical with a central axis as a center and in which compressed air is configured to flow toward a downstream side;
an outer shell which covers an end portion on an upstream side of the combustor basket; and
a combustor nozzle in the combustor basket,
wherein:
the outer shell defines a compressed air flow path which is configured to introduce the compressed air into the combustor basket between the outer shell and the combustor basket;
the compressed air flow path is configured to receive compressed air from the upstream side, reverse a flow of the compressed air to the downstream side at the end portion on the upstream side of the combustor basket, and then introduce the compressed air into the combustor basket;
the combustor nozzle includes a nozzle main body extending along an axis,
the nozzle main body includes:
a fuel passage which extends along the axis and through which fuel is configured to flow;
a plurality of fuel ejection passages which extend to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the fuel passage and are configured to eject the fuel from the outer circumferential surface of the nozzle main body;
an air flow passage which extends in an axial direction in which the axis extends and through which purge air is configured to flow;
an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured to eject the purge air from the center of the distal end of the nozzle main body; and
an air intake part which connects the outer circumferential surface of the nozzle main body and the air flow passage and is configured to take in the purge air from the outer circumferential surface of the nozzle main body, and
wherein:
the air intake part is defined in the nozzle main body at a portion on a radial outer side with respect to the central axis of the combustor basket; and
the air ejection passage includes:
a plurality of upstream-side air ejection passages connected to the air flow passage;
an air cavity connected to downstream sides of the plurality of upstream-side air ejection passages; and
a downstream-side air ejection passage connecting the air cavity and the center of the distal end of the nozzle main body, the plurality of fuel ejection passages and the plurality of upstream-side air ejection passages having different circumferential positions with respect to the axis and intersecting each other when viewed from a radial direction with respect to the axis.

12. The combustor according to claim 11 , wherein:
the combustor nozzle includes a turning vane on the outer circumferential surface of the

Assignees

• Mitsubishi Hitachi Power Sys Ltd
• Mitsubishi Power Ltd

Inventors

• Miyamoto Kenji
• Taniguchi Kenta
• Inoue Kei
• Domen Shohei
• Ichikawa Yuichi
• Tanimura Satoshi

Classifications

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F05D2220/32

  in gas turbines · CPC title