Turbomachine having a seal device

Patent metadata

Field	Value
Publication number	US-10240474-B2
Application number	US-201615144974-A
Country	US
Kind code	B2
Filing date	May 3, 2016
Priority date	May 8, 2015
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A turbomachine includes a seal device for sealing a gap between two components, with a plurality of sealing elements tippable in the direction of a relative displacement of the components. The sealing elements are mounted on one of the components and bridge the gap where the device has prestressing elements, by which the tippable sealing elements are prestressed against a respective sealing edge of the components. The prestressing elements are each supported at a front support point and a back support point of the component on the mounting side, these points being distanced from one another in the axial direction and in the radial direction of the turbomachine where the front support point is disposed radially outside and the back support point is disposed radially inside with respect to the mounting.

First claim

What is claimed is:

1. A turbomachine having a seal device for sealing a gap between two stator components, having a plurality of sealing elements that are mounted on one of the stator components and bridge the gap, and having a plurality of prestressing elements, by which the sealing elements are prestressed against a respective sealing edge of the stator components, wherein the prestressing elements are disposed on the stator component on the mounting side, and the sealing edge of the stator component on the mounting side is next to the mounting and the sealing edge of the stator component without the mounting is far from the mounting, wherein the sealing edge next to the mounting is disposed between the mounting and the sealing edge far from the mounting, and wherein the prestressing elements engage, between the sealing edges, on the sealing elements near the sealing edge next to the mounting and at a distance from the sealing edge far from the mounting, wherein the prestressing elements are each supported at a front support point and a back support point of the stator component on the mounting side, which are distanced from one another in the axial direction and radial direction of the turbomachine, wherein the front support point is disposed radially outside and the back support point is disposed radially inside with respect to the mounting, wherein the front support point is upstream of the back support point along a direction of gas flow.

2. The turbomachine according to claim 1 , wherein the prestressing elements are each taken up by a hook-like support section in a peripheral groove of the mounting-side stator component, and the support points are formed by two opposite-lying sections of the groove walls displaced radially relative to one another.

3. The turbomachine according to claim 1 , wherein the prestressing elements each have a U-shaped spring section.

4. The turbomachine according to claim 3 , wherein the spring section is bent.

5. The turbomachine according to claim 3 , wherein the spring section and the hook-like support section have two opposite-lying end segments, and the sealing elements are mounted therebetween.

6. The turbomachine according to claim 5 , wherein one of the end segment of the support section is supported on the back support point and the end segment of the spring section engages on the sealing element.

7. The turbomachine according to claim 2 , wherein the sealing elements are mounted by mounting pins extending in the axial direction through the peripheral groove.

8. The turbomachine according to claim 1 , wherein several prestressing elements are each assigned to one sealing element.

9. The turbomachine according to claim 1 , wherein a distance ratio between a force introduction point at which the prestressing element introduces a force onto the sealing element, relative to the sealing edge next to the mounting and to the sealing edge far from the mounting, is smaller than 1:5.

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred
• Kirchner Daniel

Classifications

• F05D2220/32

  in gas turbines · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title