Compressor with stator vane configuration in vicinity of bleed structure, and gas turbine engine

Patent metadata

Field	Value
Publication number	US-10774750-B2
Application number	US-201414894077-A
Country	US
Kind code	B2
Filing date	Feb 7, 2014
Priority date	Oct 17, 2013
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

A compressor includes: a plurality of vanes at a vane stage provided to a rotor casing demarcating the primary duct; an air bleed chamber casing that demarcates an air bleed chamber interconnecting with the primary duct; and an air bleed tubing connected to the air bleed chamber casing. Of the plurality of vanes, when a plurality of vanes positioned at a region including the position in the peripheral direction corresponding to the air bleed tubing are a first vane group and a plurality of vanes other than the first vane group are a second vane group, the spacing between the ends at the outside in the radial direction of the vanes that are adjacent in the first vane group is closer than the spacing between the ends at the outside in the radial direction of the vanes that are adjacent in the second vane group.

First claim

The invention claimed is:

1. A compressor comprising:
a rotor which is rotatable around an axis;
a rotor casing which surrounds the rotor from an outer peripheral side thereof to allow a main flow path of a fluid to be defined between the rotor casing and the rotor;
a stator blade stage including a circular array of a plurality of stator blades extending radially inward from the rotor casing, the plurality of stator blades being provided with intervals therebetween in a circumferential direction of the rotor casing so as to be directed toward an inside of the rotor casing;
a bleed chamber casing which is provided on an outer peripheral side of the rotor casing, the bleed chamber casing defining a bleed chamber that communicates with the main flow path via a slot that is formed in the rotor casing and extends in the circumferential direction on a downstream side of the stator blade stage, the stator blade stage disposed immediately upstream from the slot; and
a pipe which is connected to the bleed chamber casing from an outer peripheral side thereof and has a bleed flow path formed therein, the bleed flow path being configured to guide the fluid in the bleed chamber to an outside,
wherein a first stator blade group is defined by a first plurality of the stator blades positioned in a region corresponding to a circumferential position that includes the pipe, the first plurality of the stator blades being equally spaced from one another in the circumferential direction,
wherein a second stator blade group is defined by a second plurality of the stator blades that exclude the first stator blade group, the second plurality of the stator blades being equally spaced from one another in the circumferential direction,
wherein each stator blade in the circular array of the plurality of stator blades is included in one of the first plurality of the stator blades and the second plurality of the stator blades,
wherein an interval between outside end portions of adjacent stator blades in the first stator blade group is smaller than an interval between outside end portions of adjacent stator blades in the second stator blade group, and
wherein a circumferential region of the stator blade stage occupied by the first stator bade group is smaller than a circumferential region of the stator blade stage occupied by the second stator blade croup.

2. The compressor according to claim 1 , wherein at least two of the stator blades of the first plurality of the stator blades, which are adjacent to each other in the circumferential direction and in the first stator blade group, are provided so as to become further apart from each other in a radially outward direction.

3. The compressor according to claim 1 , wherein the stator bade stage is disposed immediately upstream from the slot, and wherein an interval between inside end portions of the adjacent stator blades in the first stator blade group is smaller than an interval between inside end portions of the adjacent stator blades in the second stator blade group.

4. The compressor according to claim 1 , wherein at least two stator blades of the first plurality of the stator blades, which are adjacent to each other in the circumferential direction and in the first stator blade group, are provided so as to become closer to each other in a radially outward direction.

5. A gas turbine comprising: the compressor according to claim 1 , the compressor compressing air as the fluid by rotating the rotor; a combustor which generates combustion gas by combusting a fuel in the compressed air that is compressed by the compressor; and a turbine which is driven by the combustion gas from the combustor.

6. A compressor comprising:
a rotor which is rotatable around an axis;
a rotor casing which surrounds the rotor from an outer peripheral side thereof to allow a main flow path of a fluid to be defined between the rotor casing and the rotor;
a plurality of stator blade stages extending radially inward from an inner peripheral surface of the rotor casing, wherein a first stator blade stage of the stator blade stages includes a circular array of a plurality of stator blades extending radially inward from the rotor casing, the plurality of stator blades being provided with intervals therebetween in a circumferential direction of the rotor casing so as to be directed toward an inside of the rotor casing;
a bleedchamber casing which is provided on the outer peripheral side of the rotor casing, the bleed chamber casing defining a bleed chamber that communicates with the main flow path via a slot that is formed in the rotor casing and extends in the circumferential direction on a downstream side of the stator blades; and
a pipe which is connected to the bleed chamber casing from an outer peripheral side thereof and has a bleed flow path formed therein, the bleed flow path being configured to guide the fluid in the bleed chamber to an outside,
wherein the first stator blade stage is disposed immediately upstream from the slot,
wherein a first stator blade group is defined by a first plurality of the stator blades positioned in a region corresponding to a circumferential position that includes the pipe, the first plurality of the stator blades being equally spaced from one another in the circumferential direction,
wherein a second stator blade group is defined by a second plurality of the stator blades that exclude the first stator blade group, the second plurality of the stator blades being equally spaced from one another in the circumferential direction,
wherein each stator blade in the circular array of the plurality of stator blades is included in one of the first plurality of the stator blades and the second plurality of the stator blades,
wherein an interval between outside end portions of adjacent stator blades in the first stator blade group is smaller than an interval between outside end portions of adjacent stator blades in the second stator blade group, and
wherein a circumferential region of the first stator blade stage occupied by the first stator blade group is smaller than a circumferential region of the first stator blade stage occupied by the second stator blade group.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Walker Thomas

Classifications

• F04D29/666 Primary

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F04D29/544

  Blade shapes · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title