Gas turbine engine with a turbine blade tip clearance control system

Patent metadata

Field	Value
Publication number	US-10830083-B2
Application number	US-201415515169-A
Country	US
Kind code	B2
Filing date	Oct 23, 2014
Priority date	Oct 23, 2014
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A gas turbine engine having a turbine blade tip clearance control system for increasing the efficiency of the engine by reducing the gap between turbine blade tips and radially outward ring segments is disclosed. The turbine blade tip clearance control system may include one or more clearance control bands positioned radially outward of inner surfaces of ring segments and bearing against at least one outer surface of the ring segments to limit radial movement of the ring segments. During operation, the clearance control band limits radial movement of the ring segments, and the turbine blade tips do not have a pinch point during start-up transient conditions. In addition, the smallest gap during turbine engine operation may be found at steady state operation of the gas turbine engine. Thus, the clearance control system can set the gap between turbine blade tips and ring segments to be zero at steady state operation.

First claim

We claim:

1. A gas turbine engine comprising:
a turbine assembly formed from a rotor assembly having at least one turbine blade formed from a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side, a tip at a first end and a platform coupled to a second end of the generally elongated airfoil opposite to the first end;
a ring segment positioned radially outward from the tip of the at least one turbine blade, wherein the ring segment is aligned in a circumferentially extending row forming a ring around a travel path of the at least one turbine blade and wherein the ring segment includes an inner surface forming a portion of a hot gas path within the turbine assembly;
at least one clearance control band configured as a strip and positioned radially outward of the inner surface of the ring segment and bearing against an outer surface of the ring segment to limit radial movement of the ring segment;
wherein the at least one clearance control band forms a ring radially outward of the inner surface of the ring segment,
wherein the ring segment is a single piece,
wherein a first upstream receiver channel is positioned on an upstream aspect of the ring segment and extends radially outward from the outer surface of the ring segment to contain an upstream edge of the at least one clearance control band,
wherein a first downstream receiver channel is positioned on a downstream aspect of the ring segment and extends radially outward from the outer surface of the ring segment to contain a downstream edge of the at least one clearance control band,
wherein the at least one clearance control band has a lower coefficient of thermal expansion than a material forming the ring segment,
wherein the at least one clearance control band is formed from an upper half and a lower half,
wherein an upper pin extends radially outward from the upper half clearance control band and is positioned at a top dead center position to secure the upper half clearance control band, and
wherein a lower pin extends radially outward from the lower half clearance control band and is positioned at a bottom dead center position to secure the lower half clearance control band.

2. The gas turbine engine of claim 1 , wherein the ring segment includes an upstream bearing surface and a downstream bearing surface configured to engage the at least one clearance control band.

3. The gas turbine engine of claim 1 , wherein the first upstream receiver channel is formed from an upstream bearing surface and an upstream outer containment surface, and wherein the first downstream receiver channel is formed from a downstream bearing surface and a downstream outer containment surface.

4. The gas turbine engine of claim 3 , wherein at least one upstream support arm extending radially outward from the ring segment and at least one downstream support arm extends radially outward from the ring segment, wherein the at least one upstream support arm houses the first upstream receiver channel and the at least one downstream support arm houses the first downstream receiver channel.

5. The gas turbine engine of claim 1 , wherein the upper and lower halves of the at least one clearance control band are coupled together at a first intersection at a first horizontally positioned joint and are coupled together at a second intersection at a second horizontally positioned joint.

6. The gas turbine engine of claim 5 , wherein at least one of the first and second joints are coupled together via at least one locking pin extending through an orifice in a first joint connection block and an orifice in a second joint connection block.

7. The gas turbine engine of claim 1 , wherein each of the upper and lower pins comprises a head and a body, and wherein the head has a larger cross-sectional area than the body and is positioned radially outward from the body and is secured by a bearing surface on an adjacent turbine component.

8. The gas turbine engine of claim 1 , further comprising a side wave spring positioned between a radially outward facing surface of a turbine vane carrier and a radially inward facing surface of the ring segment, the side wave spring being configured to bias the ring segment radially outward.

Assignees

• Siemens Energy Inc

Inventors

• Zhang Jiping
• Pepperman Barton M

Classifications

• F01D11/18 Primary

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F05D2300/50212

  dissimilar · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D11/16

  by self-adjusting means (F01D11/12 takes precedence) · CPC title