Turbomachine stage

Patent metadata

Field	Value
Publication number	US-10415425-B2
Application number	US-201715407416-A
Country	US
Kind code	B2
Filing date	Jan 17, 2017
Priority date	Jan 19, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

The invention relates to a turbomachine including:
a guide baffle, whose s v guide blades are situated on c guide blade carriers; and
an adjacent moving baffle including s b moving blades;
the guide baffle n v including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle n b including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient
∑ i = 1 n v ⁢ ⁢ m i s v - c
of sum

∑ i = 1 n v ⁢ ⁢ m i
of the masses of all impulse bodies of the guide baffle divided by the difference (s v −c) of the number s v of all guide blades minus the number c of all guide blade carriers amounts to at least 1.5 times quotient

∑ j = 1 n b ⁢ ⁢ m j s b
of sum

∑ j = 1 n b ⁢ ⁢ m j
of the masses of all impulse bodies of the moving baffle divided by the number s b of all moving blades

(

∑

i
=
1

n
v

⁢

⁢

m
i

s
v

-
c

≥

1.5
·

∑

j
=
1

n
b

⁢

⁢

m
j

s
b

)

.

First claim

What is claimed is:

1. A turbomachine stage comprising:
a guide baffle, whose s v guide blades are situated on c guide blade carriers; and
an adjacent moving baffle including s b moving blades;
the guide baffle including n v impulse bodies situated in a cavity system of the guide baffle with movement play with respect to impulse contact;
the moving baffle including n b impulse bodies situated in a cavity system of the moving baffle with movement play with respect to impulse contact; and quotient

∑

i
=
1

n
v

⁢

m
i

s
v

-
c

of sum

∑

i
=
1

n
v

⁢

m
i

of the masses of all impulse bodies of the guide baffle divided by difference (s v −c) of number s v of all guide blades minus number c of all guide blade carriers amounting to at least 1.5 times quotient

∑

j
=
1

n
b

⁢

m
j

s
b

of sum

∑

j
=
1

n
b

⁢

m
j

of the masses of all impulse bodies of the moving baffle divided by number s b of all moving blades

(

∑

i
=
1

n
v

⁢

m
i

s
v

-
c

≥

1.5
·

∑

j
=
1

n
b

⁢

m
j

s
b

)

.

2. The turbomachine stage as recited in claim 1 wherein the moving baffle is situated upstream or downstream from the guide baffle.

3. The turbomachine stage as recited in claim 1 wherein the turbomachine stage is a compressor or turbine stage.

4. The turbomachine stage as recited in claim 3 wherein the turbomachine stage is a gas turbine turbomachine stage.

5. The turbomachine stage as recited in claim 1 wherein at least two of the guide blades are situated on at least one of the guide blade carriers.

6. The turbomachine stage as recited in claim 5 wherein the at least two of the guide blades are situated on the guide blade carrier nondestructively removably.

7. The turbomachine stage as recited in claim 5 wherein the at least two of the guide blades are situated non-nondestructively removably attached to the guide blade carrier or designed integrally with the guide blade carrier.

8. The turbomachine stage as recited in claim 1 wherein at least one of the impulse bodies of the guide baffle or at least one of the impulse bodies of the moving baffle is spherical.

9. The turbomachine stage as recited in claim 1 wherein exactly one or at least two of the impulse bodies of the guide baffle is or are situated in at least one cavity of the cavity system of the guide baffle or exactly one or at least two of the impulse bodies of the moving baffle is or are situated in at least one cavity of the cavity system of the moving baffle.

10. The turbomachine stage as recited in claim 1 wherein at least one of the impulse bodies of the guide baffle or at least one of the impulse bodies of the moving baffle is non-captively situated in a cavity of the cavity system.

11. The turbomachine stage as recited in claim 1 wherein at least one cavity of the cavity system of the guide baffle or at least one cavity of the cavity system of the moving baffle is situated in a separately manufactured housing.

12. The turbomachine stage as recited in claim 1 wherein the cavity of the cavity system of the guide baffle or the cavity of the cavity system of the moving baffle is airtight.

13. The turbomachine stage as recited in claim 1 wherein at least one of the impulse bodies of the guide baffle is situated on a radially inner shroud, at least one of the impulse bodies of the guide baffle is situated on a vane of the guide blade, or at least one of the impulse bodies of the guide baffle is situated on a radially outer shroud of the guide baffle, or at least one of the impulse bodies of the moving baffle is situated on a radially inner shroud of the moving baffle, at least one of the impulse bodies of the moving baffle is situated on a vane of the moving blades, or at least one of the impulse bodies of the moving baffle is situated on a radially outer shroud of the moving baffle.

14. The turbomachine stage as recited in claim 13 wherein the at least one of the impulse bodies of the guide baffle is situated in the radially inner shroud, or in the vane of the guide blade, or in the radially outer shroud of the guide baffle, or the at least one of the

Assignees

• MTU Aero Engines AG

Inventors

• Schlemmer Markus
• Hartung Andreas
• Richter Karl-Hermann
• Hanrieder Herbert

Classifications

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F01D5/16

  for counteracting blade vibration · CPC title

• F01D5/26

  Antivibration means not restricted to blade form or construction or to blade-to-blade connections {or to the use of particular materials} · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title