# US 2014/0150451 A1 · Band structure and micro gas turbine having the same

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- Number: US 2014/0150451 A1
- Document ID: US20140150451A1
- Status: Published application
- Kind: A1
- Application number: 13/798,373
- Filed: 2013-03-13
- Published: 2014-06-05
- Earliest claimed: 2012-11-22
- Assignees: STX Heavy Industries, Co., Ltd.
- Inventors: Jong Gi Kim; Jin Hyung Park; Sang Min Lee; Sung Wook Heo
- Web page: https://patentgrep.com/patent/US20140150451A1

## CPC

- F01D 25/246: {Fastening of diaphragms or stator-rings}
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)

## Abstract

Disclosed are a band structure and a micro gas turbine having the same. An insert wall and a nozzle ring casing are respectively surrounded in part by a first band structure of a heat resistant material and a second band structure of a material that is identical or similar to the material of the first band structure to prevent thermal deformation of the insert wall and of the nozzle ring casing and a nozzle vane so as to maintain constant gaps between a blade tip of a turbine wheel and the insert wall and between a leading edge of the turbine wheel and the nozzle vane, thereby preventing reduction in both the power output of the turbine wheel even after a prolonged drive period and the operation efficiency of the micro gas turbine.

## Claims

### Claim 1

A band structure surrounding a portion of an outer circumference of an insert wall or a nozzle ring casing in a micro gas turbine so as to prevent the insert wall or the nozzle ring casing from being enlarged due to thermal deformation.

### Claim 2

A micro gas turbine comprising:
a turbine wheel;
a bearing casing provided in one side of the turbine wheel;
a nozzle ring casing supported by the bearing casing;
a combustor supplying combustion gas to the turbine wheel;
an insert wall disposed between the combustor and the turbine wheel to provide a channel wall for the combustion gas;
a nozzle vane provided between the insert wall and the nozzle ring casing to apply an aerodynamic force from the combustor to the turbine wheel; and
a first band structure surrounding a portion of an outer circumference of the insert wall to prevent the insert wall from being thermally deformed and enlarged.

### Claim 3 (depends on 2)

The micro gas turbine according to claim 2, further comprising a second band structure surrounding a portion of an outer circumference of the nozzle ring casing to prevent the nozzle ring casing and the nozzle vane from being thermally deformed and enlarged.