Rotor blade for a turbomachine

Patent metadata

Field	Value
Publication number	US-11098593-B2
Application number	US-201916409980-A
Country	US
Kind code	B2
Filing date	May 13, 2019
Priority date	May 18, 2018
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade having an airfoil and an inner platform radially inwardly thereof, the inner platform having a chamber formed therein which is radially outwardly bounded by an inner shroud of the inner platform and is axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform. A forward sealing plate is disposed at the forward chamber wall and extends axially forwardly away from the chamber, and a rearward sealing plate is disposed at the rearward chamber wall and extends axially rearwardly away from the chamber. Furthermore, an axial partition is disposed in the chamber, which axial partition divides the chamber into a radially inner chamber wall region and a radially outer chamber wall region and which, when viewed in an axial cross section, extends into the forward chamber wall at the level of the forward sealing plate and into the rearward chamber wall at the level of the rearward sealing plate.

First claim

What is claimed is:

1. A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade comprising:
an airfoil;
an inner platform radially inwardly of the airfoil, the inner platform having a chamber formed in the platform, the chamber being radially outwardly bounded by an inner shroud of the inner platform and axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform;
a forward sealing plate disposed at the forward chamber wall extending axially forwardly away from the chamber;
a rearward sealing plate disposed at the rearward chamber wall extending axially rearwardly away from the chamber; and
an axial partition disposed in the chamber, the axial partition dividing the chamber into a radially inner chamber wall region and a radially outer chamber wall region, the axial partition when viewed in an axial cross section, extending into the forward chamber wall at a forward sealing plate level and into the rearward chamber wall at a rearward sealing plate level;
wherein, the axial partition has a rear upper planar surface defining a rear upper plane and a rear lower planar surface defining a rear lower plane, the rearward sealing plate, without consideration of any fillet, extending at least partially between the rear upper plane and the rear lower plane at a side of the rearward chamber wall opposite the axial partition.

2. The rotor blade as recited in claim 1 , wherein the rear upper plane enters the rearward sealing plate away from any fillet.

3. The rotor blade as recited in claim 2 wherein the rearward sealing plate has a fillet on a radially inner side, the rear lower plane overlapping with the fillet.

4. The rotor blade as recited claim 1 , wherein, when viewed in an axial cross section, the axial partition extends into the forward chamber wall in such a way that, at the forward chamber wall, the axial partition has a front upper planar surface defining a front upper plane and a front lower planar surface defining a front lower plane, the forward sealing plate, without consideration of any fillet, extending at least partially between the front upper plane and the front lower plane at a side of the forward chamber wall opposite the axial partition.

5. The rotor blade as recited in claim 4 wherein the forward sealing plate has a fillet on a radially inner side, the lower front plane entering the forward sealing plate through the fillet.

6. The rotor blade as recited in claim 4 wherein the front upper plane and the rear upper plane are angled with respect to each other.

7. The rotor blade as recited in claim 1 wherein the axial partition is inserted as a separate part in the chamber.

8. The rotor blade as recited in claim 1 wherein a portion of the forward sealing plate is disposed radially inwardly of the rearward sealing plate.

9. A turbine module comprising the rotor blade as recited in claim 1 .

10. The turbine module as recited in claim 9 wherein a rotor blade ring, on which the rotor blade is disposed, is disposed upstream of a downstream stator vane ring having a downstream stator vane, the rearward sealing plate of the rotor blade being disposed radially between a downstream stator vane inner platform and a sealing fin of the downstream stator vane ring.

11. The turbine module as recited in claim 9 wherein a rotor blade ring, on which the rotor blade is disposed, is disposed downstream of an upstream stator vane ring having an upstream stator vane, the upstream sealing plate of the rotor blade being disposed radially between an upstream stator vane inner platform and a sealing fin of the upstream stator vane ring.

12. The rotor blade as recited in claim 1 wherein, when viewed in the axial cross section, the axial partition is bent between the forward chamber wall and the rearward chamber wall.

13. The rotor blade as recited in claim 1 wherein the axial partition is integrally formed as a single piece with the remainder of the rotor blade.

14. A method for operating a turbine module as recited in claim 9 comprising flowing hot gas from the hot gas duct of the turbomachine into a radially outer chamber wall region of the rotor blade, and flowing a sealing fluid from a disk edge region into the radially inner chamber wall region.

15. The method as recited in claim 14 wherein a value of a pressure developing in the radially inner chamber wall region differs no more than 20% from that of a pressure developing in the radially outer chamber wall region.

16. A method for using the rotor blade as recited in claim 1 comprising flowing hot gas from the hot gas duct of the turbomachine into a radially outer chamber wall region of the rotor blade, and flowing a sealing fluid from a disk edge region into the radially inner chamber wall region.

17. A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade comprising:
an airfoil;
an inner platform radially inwardly of the airfoil, the inner platform having a chamber formed in the platform, the chamber being radially outwardly bounded by an inner shroud of the inner platform and axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform;
a forward sealing plate disposed at the forward chamber wall extending axially forwardly away from the chamber;
a rearward sealing plate disposed at the rearward chamber wall extending axially rearwardly away from the chamber; and
an axial partition disposed in the chamber, the axial partition dividing the chamber into a radially inner chamber wall region and a radially outer chamber wall region, the axial partition when viewed in an axial cross section, extending into the forward chamber wall at a forward sealing plate level and into the rearward chamber wall at a rearward sealing plate level;
wherein, when viewed in the axial cross section, the axial partition has a front upper planar surface defining a front upper plane and a front lower planar surface defining a front lower plane, the forward sealing plate, without consideration of any fillet, extending at least partially between the front upper plane and the front lower plane at a side of the forward chamber wall opposite the axial partition.

18. A rotor blade for disposition in a hot gas duct of a turbomachine, the rotor blade comprising:
an airfoil;
an inner platform radially inwardly of the airfoil, the inner platform having a chamber formed in the platform, the chamber being radially outwardly bounded by an inner shroud of the inner platform and axially bounded between a forward chamber wall and a rearward chamber wall of the inner platform;
a forward sealing plate disposed at the forward chamber wall extending axially forwardly away from the chamber;
a rearward sealing plate disposed at the rearward chamber wall extending axially rearwardly away from the chamber; and
an axial partition disposed in the chamber, the axial partition dividing the chamber into a radially inner chamber wall region and a radially outer chamber wall region, the axial partition when viewed in an axial cross section, extending into the forward chamber wall at a forward sealing plate level and into the rearward chamber wall at a rearward sealing plate level;
wherein, when viewed in the axial cross section, the axial partition is connected to the forward chamber wall at a different level than the rearward chamber wall to accommodate different levels of the forward and rearward sealing plates.

19. The rotor blade as recited in claim 18 wherein, when viewed in the axial cross section, the a

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred

Classifications

• F01D5/085

  cooling fluid circulating inside the rotor · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D11/04

  using sealing fluid, e.g. steam · CPC title